Space Administration NASA 2016SL - Auburn University

94
Colleges, Universities, Non-Academic Handbook SL 2016 NASA Student Launch National Aeronautics and Space Administration

Transcript of Space Administration NASA 2016SL - Auburn University

CollegesUniversitiesNon-Academic Handbook

SL2016NASAStudent Launch

National Aeronautics and Space Administration

Note For your convenience this document identifies Web links when available These links are correct as of this publishing however since Web links can be moved or disconnected at any time we have also provided source information as available to assist you in locating the information

Table of Contents

Timeline for NASA University Student Launch Initiative 1Acronym Dictionary 2

ProposalStatement of Work for CollegesUniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground SupportEquipment Statement of Work (SOW) 4

Vehicle Requirements 5Recovery System Requirements 7Competition and Payload Requirements 8Safety Requirements 9General Requirements 10

Proposal Requirements 12

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria 16Critical Design Review (CDR) Vehicle and Payload Experiment Criteria 20Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria 25Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria 30Post Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria 30Educational Engagement Form 31

Safety

High Power Rocket Safety Code 34Minimum Distance Table 36

Related Documents

USLI Competition Awards 38NASA Project Life Cycle 39Hazard Analysis ndash Introduction to Managing Risk 47Example Hazard Analysis 57Understanding Material Safety Data Sheets (MSDS) 63

Timeline for NASA University Student Launch Initiative (Dates are subject to change)

August 2015 7 Request for Proposal (RFP) goes out to all teams

September 201511 Electronic copy of completed proposal due to project office by 5 pm CDT to

Ian Bryant (Jacobs ESSSA Group) ianlbryantnasagov

Katie Wallace katievwallacenasagov

Julie Clift juliedcliftnasagov

October 2015 2 Awarded proposals announced 7 Kickoff and PDR QampA 23 Team web presence established

November 2015 6 Preliminary Design Review (PDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 9-20 PDR video teleconferences

December 2015 4 CDR QampA

January 201615 Critical Design Review (CDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 19-29 CDR video teleconferences

February 20163 FRR QampA

March 2016 14 Flight Readiness Review (FRR) reports presentation slides and flysheet posted to team Website

by 800 am Central Time 17-30 FRR video teleconferences

April 201613 Teams travel to Huntsville AL 13 Launch Readiness Reviews (LRR) 14 LRRrsquos and safety briefing 15 Rocket Fair and Tours of MSFC 16 Launch Day 17 Backup launch day 29 Post-Launch Assessment Review (PLAR) posted on the team Website by 800 am Central Time

May 2016Winning team announced 11

1

Acronym Dictionary

AGL=Above Ground Level

APCP=Ammonium Perchlorate Composite Propellant

CDR=Critical Design Review

CC=Centennial Challenges

CG=Center of Gravity

CP=Center of Pressure

EIT=Electronics and Information Technology

FAA=Federal Aviation Administration

FN=Foreign National

FRR=Flight Readiness Review

HEO=Human Exploration and Operations

LCO=Launch Control Officer

LRR=Launch Readiness Review

MAV=Mars Ascent Vehicle

MSDS=Material Safety Data Sheet

MSFC=Marshall Space Flight Center

NAR=National Association of Rocketry

PDR=Preliminary Design Review

PLAR=Post Launch Assessment Review

PPE=Personal Protective Equipment

RFP=Request for Proposal

RSO=Range Safety Officer

USLI=University Student Launch Initiative

SME=Subject Matter Expert

SOW=Statement of Work

STEM=Science Technology Engineering and Mathematics

TRA=Tripoli Rocketry Association

2

ProposalStatement of Work for Colleges UniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement

of Work (SOW)

1 Project Name NASA University Student Launch Initiative for colleges and universities

2 Governing Office NASA Marshall Space Flight Center Academic Affairs Office

3 Period of Performance Eight (8) calendar months

4 IntroductionThe NASA University Student Launch Initiative (USLI) is a research-based competitive and experiential

exploration project that provides relevant and cost effective research and development Additionally NASA

University Student Launch Initiative connects learners educators and communities in NASA-unique

opportunities that align with STEM Challenges under the NASA Education Science Technology Engineering

and Mathematics (STEM) Engagement line of business NASArsquos missions discoveries and assets provide

opportunities for individuals that do not exist elsewhere The project involves reaching a broach audience of

colleges and universities across the nation in an 8-month commitment to design build launch and fly a

payload(s) and vehicle components that support NASA research on high-power rockets to an altitude of

5280 feet above ground level (AGL) The challenge is based on team selection of multiple options There is

a Student Launch option that consists of 7 different experiments and a Centennial Challenge (CC) option

that consists of designing and building a Mars Ascent Vehicle (MAV) Supported by the Office of Education

Human Exploration and Operations (HEO) Mission Directorate Centennial Challenges Office and

commercial industry USLI is a unique NASA-specific opportunity to provide resources and experiences thatis built around a mission not textbook knowledge

After a competitive proposal selection process teams participate in a series of design reviews that are

submitted to NASA via a team-developed website These reviews mirror the NASA engineering design

lifecycle providing a NASA-unique experience that prepares individuals for the HEO workforce Teams must

successfully complete a Preliminary Design Review (PDR) Critical Design Review (CDR) Flight Readiness

Review (FRR) Launch Readiness Review (LRR) that includes safety briefings and an analysis of vehicle

systems ground support equipment and flight data Each team must pass a review in order to move to a

subsequent review Teams will present their PDR CDR and FRR to a review panel of scientists engineers

technicians and educators via video teleconference Review panel members the Range Safety Officer

(RSO) and Subject Matter Experts (SME) provide feedback and ask questions in order to increase the

fidelity between the USLI and research needs and will score each team according to a standard scoring

rubric The partnership of teams and NASA is win-win which not only benefits from the research conducted

by the teams but also prepares a potential future workforce familiar with the NASA Engineering Design

Lifecycle

College and university teams must successfully complete the requirements of Tasks 1 or 2 and are eligible

for awards through Student Launch Any team who wishes to incorporate additional research through the use

of a separate payload may do so The team must provide documentation in all reports and reviews oncomponents and systems outside of what is required for the project The Centennial Challenges Office will

award prizes to college university and non-academic teams for successful demonstration of the MAV (see

CC supplemental handbook) The USLI awards listed at the end of this handbook will only be given to teams

from an academic institution

4

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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41

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cal N

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PR 71

205

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e 2-

4 ldquo

The

NAS

A Pr

ojec

t Life

Cyc

lerdquo

42

Stud

ent L

aunc

h Pr

ojec

ts L

ife C

ycle

Phas

e A

Phas

e B

Phas

e C

Phas

e D

Phas

e E

Phas

e F

Acqu

isiti

on amp

Pr

elim

inar

y De

sign

Fina

l Des

ign

Fabr

icat

ion

amp

Ope

ratio

ns amp

Di

spos

alRe

quire

men

tsLa

unch

Sust

ainm

ent

Auth

ority

to P

roce

edSR

RPD

RCD

RFR

R Laun

chbull

ATP

(Aut

horit

y to

Proc

eed)

ndashFu

ndin

g is

appl

ied

to th

e co

ntra

cte

ffort

and

wor

k per

form

ance

ca

n be

gin

bullSR

R (S

yste

m R

equi

rem

ents

Rev

iew

) ndashTo

p Le

vel R

equi

rem

ents

are

conv

erte

d in

to sy

stem

re

quire

men

ts S

yste

m R

equi

rem

ents

are

revi

ewed

and

aut

horit

y is g

iven

to p

roce

ed in

to

Prel

imin

ary

Desig

n T

he N

ASA

Stud

ent L

aunc

h Pr

ojec

t ski

ps th

is st

ep

bullPD

R (P

relim

inar

y Des

ign

Revi

ew) ndash

Prel

imin

ary

Desig

n is

revi

ewed

and

aut

horit

y is g

iven

to

proc

eed

into

Fin

al D

esig

nbull

CDR

(Crit

ical

Des

ign

Revi

ew) ndash

Fina

l Des

ign

is re

view

ed a

nd a

utho

rity i

s giv

en to

pro

ceed

to

build

the

syst

em

bullFR

R (F

light

Rea

dine

ss R

evie

w) ndash

As-b

uilt

desig

n an

d te

st d

ata

are

revi

ewed

and

aut

horit

y is

give

n fo

r Lau

nch

43

Prel

imin

ary

Desi

gn R

evie

wbull

Obj

ectiv

endash

Prov

e th

e fe

asib

ility

to b

uild

and

laun

ch th

e ro

cket

pay

load

des

ign

ndash

Prov

e th

at a

ll sy

stem

requ

irem

ents

will

be

met

ndash

Rece

ive

auth

ority

to p

roce

ed to

the

Fina

l Des

ign

Phas

ebull

Typi

cal P

rodu

cts (

Vehi

cle

and

Payl

oad)

ndashSc

hedu

le (d

esig

n b

uild

tes

t)ndash

Cost

Bud

get S

tate

men

tndash

Prel

imin

ary

Desig

n Di

scus

sion

bullDr

awin

gs s

ketc

hes

bullId

entif

icatio

n an

d di

scus

sion

of co

mpo

nent

sbull

Anal

yses

(suc

h as

Veh

icle

Traj

ecto

ry P

redi

ctio

ns)

bullRi

sks

bullM

ass S

tate

men

t and

Mas

s Mar

gin

ndashM

issio

n Pr

ofile

(Con

cept

of O

pera

tions

)ndash

Inte

rfac

es (w

ithin

the

syst

em an

d ex

tern

al to

the

syst

em)

ndashTe

st a

nd V

erifi

catio

n Pl

anndash

Gro

und

Supp

ort E

quip

men

t Des

igns

Ide

ntifi

catio

nndash

Safe

ty F

eatu

res

44

Criti

cal D

esig

n Re

view

bullO

bjec

tive

ndashCo

mpl

ete

the

final

des

ign

of th

e ro

cket

pay

load

sys

tem

ndashRe

ceiv

e au

thor

ity to

pro

ceed

into

Fab

ricat

ion

and

Verif

icat

ion

phas

e

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

PDR

Deliv

erab

les

(mat

ured

to re

flect

the

final

des

ign)

ndashRe

port

and

dis

cuss

com

plet

ed te

sts

ndashPr

oced

ures

and

Che

cklis

ts

45

Flig

ht R

eadi

ness

Rev

iew

bullO

bjec

tive

ndashPr

ove

that

the

Rock

etP

aylo

ad Sy

stem

has

bee

n fu

lly b

uilt

test

ed a

nd v

erifi

ed

to m

eet t

he sy

stem

requ

irem

ents

ndashPr

ove

that

all

syst

em re

quire

men

ts h

ave

been

or w

ill b

e m

etndash

Rece

ive

auth

ority

to La

unch

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

Sche

dule

ndashCo

st S

tate

men

tndash

Desig

n O

verv

iew

bullKe

y com

pone

nts

bullKe

y dra

win

gs an

d la

yout

sbull

Traj

ecto

ry an

d ot

her k

ey a

naly

ses

bullM

ass S

tate

men

t bull

Rem

aini

ng R

isks

ndashM

issio

n Pr

ofile

ndash

Pres

enta

tion

and

anal

ysis

of te

st d

ata

ndashSy

stem

Req

uire

men

ts V

erifi

catio

nndash

Gro

und

Supp

ort E

quip

men

t ndash

Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Per

sonn

el

expo

sure

to

high

vol

tage

Con

tact

with

en

ergi

zed

lam

p ba

nk c

ircu

its

Dea

th o

r se

vere

pe

rson

nel i

njur

y 1C

1

D

urin

g te

st o

pera

tion

lam

p ba

nks

circ

uits

will

be

ener

gize

d on

ly w

hen

no

pers

onne

l are

insi

de c

ham

ber

2

D

oor

to c

ham

ber

wil

l be

clos

ed

prio

r to

ene

rgiz

ing

circ

uits

3

T

S30

0 ac

cess

con

trol

s ar

e in

pl

ace

for

the

test

1

304-

TC

P-0

16 S

ectio

n 3

13

requ

ires

di

sabl

ing

heat

er e

lect

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l cir

cuit

bef

ore

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r 2

P

er 3

04-T

CP

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tes

ts w

ill o

nly

be

perf

orm

ed u

nder

per

sona

l dir

ectio

n of

Tes

t E

ngin

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3

Acc

ess

cont

rols

for

this

test

are

in

clud

ed in

304

-TC

P-0

16 T

hese

incl

ude

o

L

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Eas

t Tes

t Are

a G

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6 a

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urn

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Lig

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ight

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o

Ver

ify

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o

V

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M

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o be

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the

Des

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304-

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Inst

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Tes

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Rem

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rdquo S

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1

2

304-

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ham

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Ven

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+ M

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the

pane

l

1E

60

Haz

ard

C

ause

E

ffec

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re-

RA

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Mit

igat

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Ver

ific

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n P

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3

Atte

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and

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estr

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una

utho

rize

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4

Fir

e D

ept

to b

e no

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w

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whi

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tify

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prio

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ing

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ope

rati

on l

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s ci

rcui

ts w

ill b

e en

ergi

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only

whe

n no

pe

rson

nel a

re in

side

cha

mbe

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2

Doo

r to

cha

mbe

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ill c

lose

d pr

ior

to e

nerg

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3

De s

igna

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pers

onne

l will

wea

r

leat

her

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es to

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dle

calib

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n pl

ate

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equi

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1

304-

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ectio

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requ

ires

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sabl

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lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r

2

Per

304

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P-0

16 t

ests

wil

l onl

y be

pe

rfor

med

und

er p

erso

nal d

irec

tion

of T

est

Eng

inee

r 3

30

4-T

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Sec

tion

14

Haz

ards

and

C

ontr

ols

req

uire

s in

sula

ted

glov

es a

s re

quir

ed

if h

ot it

ems

need

to b

e ha

ndle

d

3E

61

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Fai

lure

of

pres

sure

sy

stem

s

Ove

r-pr

essu

riza

tion

Per

sonn

el in

jury

Equ

ipm

ent

dam

age

1C

1

TS

300

faci

lity

pres

sure

sys

tem

s ar

e ce

rtif

ied

2

P

er E

T10

test

eng

inee

r h

igh

puri

ty a

ir s

yste

m w

ill b

e us

ed a

t lt 1

50

psig

ope

rati

ng p

ress

ure

ther

efor

e ce

rtif

icat

ion

not r

equi

red

3

A

ll n

on-c

erti

fied

test

equ

ipm

ent i

s pn

eum

atic

ally

pre

ssur

e te

sted

to 1

50

of

Max

imum

All

owab

le W

orki

ng P

ress

ure

(MA

WP

)

1

Per

the

MS

FC

Pre

ssur

e S

yste

ms

Rep

ortin

g T

ool (

PS

RT

) f

acili

ty s

yste

ms

have

be

en r

ecer

tifie

d un

der

TL

WT

-CE

RT

-10-

TS

300-

RR

2002

unt

il 3

320

20 T

he

cert

ific

atio

n in

clud

es G

aseo

us H

eliu

m G

aseo

us

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roge

n G

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us N

itro

gen

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h Pu

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d H

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gen

and

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uid

Nitr

ogen

sys

tem

s

2

304-

TC

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tep

21

14 r

equi

res

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nd S

tage

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HO

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o be

L

oade

d to

75p

sig

3

S

ee P

ress

ure

Tes

t Rep

ort P

TR

-001

455

(App

endi

x A

) A

ll no

n-ce

rtif

ied

equi

pmen

t has

a

min

imum

fac

tor

of s

afet

y of

41

1E

Foa

m p

anel

ca

tche

s fi

re

duri

ng te

stin

g

Tes

t req

uire

s hi

gh

heat

wit

h po

ssib

ility

of

pane

l bu

rnin

g

Rel

ease

of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

ion

requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

hed

Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

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ver

y lit

tle

or n

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sidu

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asse

s or

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ors

rem

ain

1

A m

inim

um v

enti

lati

on o

f th

e ch

ambe

r sh

ould

the

foam

pan

el b

urn

duri

ng o

r af

ter

test

ing

has

been

est

ablis

hed

by p

roce

dure

304

-T

CP

-016

whi

ch r

equi

res

the

min

imum

10

min

ute

vent

ilatio

n be

fore

per

sonn

el a

re a

llow

ed

to e

nter

Add

ition

ally

if

any

abno

rmal

ities

are

ob

serv

ed th

e In

dust

rial

Hea

lth r

epre

sent

ativ

e w

ill b

e ca

lled

to p

erfo

rm a

dditi

onal

air

sa

mpl

ing

befo

re p

erso

nnel

ent

ry

1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

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ON

E

SECT

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C14

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510-

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

Note For your convenience this document identifies Web links when available These links are correct as of this publishing however since Web links can be moved or disconnected at any time we have also provided source information as available to assist you in locating the information

Table of Contents

Timeline for NASA University Student Launch Initiative 1Acronym Dictionary 2

ProposalStatement of Work for CollegesUniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground SupportEquipment Statement of Work (SOW) 4

Vehicle Requirements 5Recovery System Requirements 7Competition and Payload Requirements 8Safety Requirements 9General Requirements 10

Proposal Requirements 12

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria 16Critical Design Review (CDR) Vehicle and Payload Experiment Criteria 20Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria 25Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria 30Post Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria 30Educational Engagement Form 31

Safety

High Power Rocket Safety Code 34Minimum Distance Table 36

Related Documents

USLI Competition Awards 38NASA Project Life Cycle 39Hazard Analysis ndash Introduction to Managing Risk 47Example Hazard Analysis 57Understanding Material Safety Data Sheets (MSDS) 63

Timeline for NASA University Student Launch Initiative (Dates are subject to change)

August 2015 7 Request for Proposal (RFP) goes out to all teams

September 201511 Electronic copy of completed proposal due to project office by 5 pm CDT to

Ian Bryant (Jacobs ESSSA Group) ianlbryantnasagov

Katie Wallace katievwallacenasagov

Julie Clift juliedcliftnasagov

October 2015 2 Awarded proposals announced 7 Kickoff and PDR QampA 23 Team web presence established

November 2015 6 Preliminary Design Review (PDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 9-20 PDR video teleconferences

December 2015 4 CDR QampA

January 201615 Critical Design Review (CDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 19-29 CDR video teleconferences

February 20163 FRR QampA

March 2016 14 Flight Readiness Review (FRR) reports presentation slides and flysheet posted to team Website

by 800 am Central Time 17-30 FRR video teleconferences

April 201613 Teams travel to Huntsville AL 13 Launch Readiness Reviews (LRR) 14 LRRrsquos and safety briefing 15 Rocket Fair and Tours of MSFC 16 Launch Day 17 Backup launch day 29 Post-Launch Assessment Review (PLAR) posted on the team Website by 800 am Central Time

May 2016Winning team announced 11

1

Acronym Dictionary

AGL=Above Ground Level

APCP=Ammonium Perchlorate Composite Propellant

CDR=Critical Design Review

CC=Centennial Challenges

CG=Center of Gravity

CP=Center of Pressure

EIT=Electronics and Information Technology

FAA=Federal Aviation Administration

FN=Foreign National

FRR=Flight Readiness Review

HEO=Human Exploration and Operations

LCO=Launch Control Officer

LRR=Launch Readiness Review

MAV=Mars Ascent Vehicle

MSDS=Material Safety Data Sheet

MSFC=Marshall Space Flight Center

NAR=National Association of Rocketry

PDR=Preliminary Design Review

PLAR=Post Launch Assessment Review

PPE=Personal Protective Equipment

RFP=Request for Proposal

RSO=Range Safety Officer

USLI=University Student Launch Initiative

SME=Subject Matter Expert

SOW=Statement of Work

STEM=Science Technology Engineering and Mathematics

TRA=Tripoli Rocketry Association

2

ProposalStatement of Work for Colleges UniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement

of Work (SOW)

1 Project Name NASA University Student Launch Initiative for colleges and universities

2 Governing Office NASA Marshall Space Flight Center Academic Affairs Office

3 Period of Performance Eight (8) calendar months

4 IntroductionThe NASA University Student Launch Initiative (USLI) is a research-based competitive and experiential

exploration project that provides relevant and cost effective research and development Additionally NASA

University Student Launch Initiative connects learners educators and communities in NASA-unique

opportunities that align with STEM Challenges under the NASA Education Science Technology Engineering

and Mathematics (STEM) Engagement line of business NASArsquos missions discoveries and assets provide

opportunities for individuals that do not exist elsewhere The project involves reaching a broach audience of

colleges and universities across the nation in an 8-month commitment to design build launch and fly a

payload(s) and vehicle components that support NASA research on high-power rockets to an altitude of

5280 feet above ground level (AGL) The challenge is based on team selection of multiple options There is

a Student Launch option that consists of 7 different experiments and a Centennial Challenge (CC) option

that consists of designing and building a Mars Ascent Vehicle (MAV) Supported by the Office of Education

Human Exploration and Operations (HEO) Mission Directorate Centennial Challenges Office and

commercial industry USLI is a unique NASA-specific opportunity to provide resources and experiences thatis built around a mission not textbook knowledge

After a competitive proposal selection process teams participate in a series of design reviews that are

submitted to NASA via a team-developed website These reviews mirror the NASA engineering design

lifecycle providing a NASA-unique experience that prepares individuals for the HEO workforce Teams must

successfully complete a Preliminary Design Review (PDR) Critical Design Review (CDR) Flight Readiness

Review (FRR) Launch Readiness Review (LRR) that includes safety briefings and an analysis of vehicle

systems ground support equipment and flight data Each team must pass a review in order to move to a

subsequent review Teams will present their PDR CDR and FRR to a review panel of scientists engineers

technicians and educators via video teleconference Review panel members the Range Safety Officer

(RSO) and Subject Matter Experts (SME) provide feedback and ask questions in order to increase the

fidelity between the USLI and research needs and will score each team according to a standard scoring

rubric The partnership of teams and NASA is win-win which not only benefits from the research conducted

by the teams but also prepares a potential future workforce familiar with the NASA Engineering Design

Lifecycle

College and university teams must successfully complete the requirements of Tasks 1 or 2 and are eligible

for awards through Student Launch Any team who wishes to incorporate additional research through the use

of a separate payload may do so The team must provide documentation in all reports and reviews oncomponents and systems outside of what is required for the project The Centennial Challenges Office will

award prizes to college university and non-academic teams for successful demonstration of the MAV (see

CC supplemental handbook) The USLI awards listed at the end of this handbook will only be given to teams

from an academic institution

4

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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A Pr

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42

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43

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44

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45

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erifi

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edur

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s

46

Haza

rd A

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sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

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r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

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e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

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ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

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iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

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41

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Und

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63

Wha

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SD

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Mat

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Dat

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(M

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man

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64

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diffe

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65

Req

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Id

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haz

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C

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Exp

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66

Req

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67

Impo

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Con

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68

Impo

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Age

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The

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Nat

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at

rela

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69

Impo

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Age

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N

FPA

Th

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An

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70

NFP

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71

Impo

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Age

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N

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The

Nat

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agen

cy o

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Pub

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Se

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

Table of Contents

Timeline for NASA University Student Launch Initiative 1Acronym Dictionary 2

ProposalStatement of Work for CollegesUniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground SupportEquipment Statement of Work (SOW) 4

Vehicle Requirements 5Recovery System Requirements 7Competition and Payload Requirements 8Safety Requirements 9General Requirements 10

Proposal Requirements 12

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria 16Critical Design Review (CDR) Vehicle and Payload Experiment Criteria 20Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria 25Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria 30Post Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria 30Educational Engagement Form 31

Safety

High Power Rocket Safety Code 34Minimum Distance Table 36

Related Documents

USLI Competition Awards 38NASA Project Life Cycle 39Hazard Analysis ndash Introduction to Managing Risk 47Example Hazard Analysis 57Understanding Material Safety Data Sheets (MSDS) 63

Timeline for NASA University Student Launch Initiative (Dates are subject to change)

August 2015 7 Request for Proposal (RFP) goes out to all teams

September 201511 Electronic copy of completed proposal due to project office by 5 pm CDT to

Ian Bryant (Jacobs ESSSA Group) ianlbryantnasagov

Katie Wallace katievwallacenasagov

Julie Clift juliedcliftnasagov

October 2015 2 Awarded proposals announced 7 Kickoff and PDR QampA 23 Team web presence established

November 2015 6 Preliminary Design Review (PDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 9-20 PDR video teleconferences

December 2015 4 CDR QampA

January 201615 Critical Design Review (CDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 19-29 CDR video teleconferences

February 20163 FRR QampA

March 2016 14 Flight Readiness Review (FRR) reports presentation slides and flysheet posted to team Website

by 800 am Central Time 17-30 FRR video teleconferences

April 201613 Teams travel to Huntsville AL 13 Launch Readiness Reviews (LRR) 14 LRRrsquos and safety briefing 15 Rocket Fair and Tours of MSFC 16 Launch Day 17 Backup launch day 29 Post-Launch Assessment Review (PLAR) posted on the team Website by 800 am Central Time

May 2016Winning team announced 11

1

Acronym Dictionary

AGL=Above Ground Level

APCP=Ammonium Perchlorate Composite Propellant

CDR=Critical Design Review

CC=Centennial Challenges

CG=Center of Gravity

CP=Center of Pressure

EIT=Electronics and Information Technology

FAA=Federal Aviation Administration

FN=Foreign National

FRR=Flight Readiness Review

HEO=Human Exploration and Operations

LCO=Launch Control Officer

LRR=Launch Readiness Review

MAV=Mars Ascent Vehicle

MSDS=Material Safety Data Sheet

MSFC=Marshall Space Flight Center

NAR=National Association of Rocketry

PDR=Preliminary Design Review

PLAR=Post Launch Assessment Review

PPE=Personal Protective Equipment

RFP=Request for Proposal

RSO=Range Safety Officer

USLI=University Student Launch Initiative

SME=Subject Matter Expert

SOW=Statement of Work

STEM=Science Technology Engineering and Mathematics

TRA=Tripoli Rocketry Association

2

ProposalStatement of Work for Colleges UniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement

of Work (SOW)

1 Project Name NASA University Student Launch Initiative for colleges and universities

2 Governing Office NASA Marshall Space Flight Center Academic Affairs Office

3 Period of Performance Eight (8) calendar months

4 IntroductionThe NASA University Student Launch Initiative (USLI) is a research-based competitive and experiential

exploration project that provides relevant and cost effective research and development Additionally NASA

University Student Launch Initiative connects learners educators and communities in NASA-unique

opportunities that align with STEM Challenges under the NASA Education Science Technology Engineering

and Mathematics (STEM) Engagement line of business NASArsquos missions discoveries and assets provide

opportunities for individuals that do not exist elsewhere The project involves reaching a broach audience of

colleges and universities across the nation in an 8-month commitment to design build launch and fly a

payload(s) and vehicle components that support NASA research on high-power rockets to an altitude of

5280 feet above ground level (AGL) The challenge is based on team selection of multiple options There is

a Student Launch option that consists of 7 different experiments and a Centennial Challenge (CC) option

that consists of designing and building a Mars Ascent Vehicle (MAV) Supported by the Office of Education

Human Exploration and Operations (HEO) Mission Directorate Centennial Challenges Office and

commercial industry USLI is a unique NASA-specific opportunity to provide resources and experiences thatis built around a mission not textbook knowledge

After a competitive proposal selection process teams participate in a series of design reviews that are

submitted to NASA via a team-developed website These reviews mirror the NASA engineering design

lifecycle providing a NASA-unique experience that prepares individuals for the HEO workforce Teams must

successfully complete a Preliminary Design Review (PDR) Critical Design Review (CDR) Flight Readiness

Review (FRR) Launch Readiness Review (LRR) that includes safety briefings and an analysis of vehicle

systems ground support equipment and flight data Each team must pass a review in order to move to a

subsequent review Teams will present their PDR CDR and FRR to a review panel of scientists engineers

technicians and educators via video teleconference Review panel members the Range Safety Officer

(RSO) and Subject Matter Experts (SME) provide feedback and ask questions in order to increase the

fidelity between the USLI and research needs and will score each team according to a standard scoring

rubric The partnership of teams and NASA is win-win which not only benefits from the research conducted

by the teams but also prepares a potential future workforce familiar with the NASA Engineering Design

Lifecycle

College and university teams must successfully complete the requirements of Tasks 1 or 2 and are eligible

for awards through Student Launch Any team who wishes to incorporate additional research through the use

of a separate payload may do so The team must provide documentation in all reports and reviews oncomponents and systems outside of what is required for the project The Centennial Challenges Office will

award prizes to college university and non-academic teams for successful demonstration of the MAV (see

CC supplemental handbook) The USLI awards listed at the end of this handbook will only be given to teams

from an academic institution

4

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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Veh

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Traj

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bullM

ass S

tate

men

t and

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s Mar

gin

ndashM

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(Con

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of O

pera

tions

)ndash

Inte

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es (w

ithin

the

syst

em an

d ex

tern

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the

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ndashTe

st a

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erifi

catio

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anndash

Gro

und

Supp

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quip

men

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igns

Ide

ntifi

catio

nndash

Safe

ty F

eatu

res

44

Criti

cal D

esig

n Re

view

bullO

bjec

tive

ndashCo

mpl

ete

the

final

des

ign

of th

e ro

cket

pay

load

sys

tem

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ceiv

e au

thor

ity to

pro

ceed

into

Fab

ricat

ion

and

Verif

icat

ion

phas

e

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

PDR

Deliv

erab

les

(mat

ured

to re

flect

the

final

des

ign)

ndashRe

port

and

dis

cuss

com

plet

ed te

sts

ndashPr

oced

ures

and

Che

cklis

ts

45

Flig

ht R

eadi

ness

Rev

iew

bullO

bjec

tive

ndashPr

ove

that

the

Rock

etP

aylo

ad Sy

stem

has

bee

n fu

lly b

uilt

test

ed a

nd v

erifi

ed

to m

eet t

he sy

stem

requ

irem

ents

ndashPr

ove

that

all

syst

em re

quire

men

ts h

ave

been

or w

ill b

e m

etndash

Rece

ive

auth

ority

to La

unch

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

Sche

dule

ndashCo

st S

tate

men

tndash

Desig

n O

verv

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bullKe

y com

pone

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bullKe

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win

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d la

yout

sbull

Traj

ecto

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d ot

her k

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naly

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bullM

ass S

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men

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Rem

aini

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isks

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ofile

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Pres

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and

anal

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of te

st d

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Req

uire

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erifi

catio

nndash

Gro

und

Supp

ort E

quip

men

t ndash

Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

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Dur

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Haz

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C

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C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Fai

lure

of

pres

sure

sy

stem

s

Ove

r-pr

essu

riza

tion

Per

sonn

el in

jury

Equ

ipm

ent

dam

age

1C

1

TS

300

faci

lity

pres

sure

sys

tem

s ar

e ce

rtif

ied

2

P

er E

T10

test

eng

inee

r h

igh

puri

ty a

ir s

yste

m w

ill b

e us

ed a

t lt 1

50

psig

ope

rati

ng p

ress

ure

ther

efor

e ce

rtif

icat

ion

not r

equi

red

3

A

ll n

on-c

erti

fied

test

equ

ipm

ent i

s pn

eum

atic

ally

pre

ssur

e te

sted

to 1

50

of

Max

imum

All

owab

le W

orki

ng P

ress

ure

(MA

WP

)

1

Per

the

MS

FC

Pre

ssur

e S

yste

ms

Rep

ortin

g T

ool (

PS

RT

) f

acili

ty s

yste

ms

have

be

en r

ecer

tifie

d un

der

TL

WT

-CE

RT

-10-

TS

300-

RR

2002

unt

il 3

320

20 T

he

cert

ific

atio

n in

clud

es G

aseo

us H

eliu

m G

aseo

us

Hyd

roge

n G

aseo

us N

itro

gen

Hig

h Pu

rity

Air

L

iqui

d H

ydro

gen

and

Liq

uid

Nitr

ogen

sys

tem

s

2

304-

TC

P-0

16 S

tep

21

14 r

equi

res

HO

R-1

2-12

8 2

nd S

tage

HP

Air

HO

R t

o be

L

oade

d to

75p

sig

3

S

ee P

ress

ure

Tes

t Rep

ort P

TR

-001

455

(App

endi

x A

) A

ll no

n-ce

rtif

ied

equi

pmen

t has

a

min

imum

fac

tor

of s

afet

y of

41

1E

Foa

m p

anel

ca

tche

s fi

re

duri

ng te

stin

g

Tes

t req

uire

s hi

gh

heat

wit

h po

ssib

ility

of

pane

l bu

rnin

g

Rel

ease

of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

ion

requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

hed

Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

s so

ver

y lit

tle

or n

o re

sidu

al g

asse

s or

vap

ors

rem

ain

1

A m

inim

um v

enti

lati

on o

f th

e ch

ambe

r sh

ould

the

foam

pan

el b

urn

duri

ng o

r af

ter

test

ing

has

been

est

ablis

hed

by p

roce

dure

304

-T

CP

-016

whi

ch r

equi

res

the

min

imum

10

min

ute

vent

ilatio

n be

fore

per

sonn

el a

re a

llow

ed

to e

nter

Add

ition

ally

if

any

abno

rmal

ities

are

ob

serv

ed th

e In

dust

rial

Hea

lth r

epre

sent

ativ

e w

ill b

e ca

lled

to p

erfo

rm a

dditi

onal

air

sa

mpl

ing

befo

re p

erso

nnel

ent

ry

1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

-3RT

ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

NE

MET

HYL

ACE

TON

E 3

-BU

TAN

ON

E M

EK

SCO

TCH

-GRI

P reg

BRA

ND

SO

LVEN

T

3 (3

M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

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RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

ress

ion

PHYS

ICAL

HAZ

ARD

S F

lam

mab

le li

quid

and

vap

or V

apor

may

cau

se fl

ash

fire

Goo

d in

fo fo

rla

belin

g co

ntai

ners

23

0

POTE

NTI

AL H

EALT

H E

FFEC

TS

INH

ALAT

ION

SH

ORT

TER

M E

XPO

SURE

irr

itatio

n n

ause

a v

omiti

ng d

iffic

ulty

bre

athi

ng

Wha

t hap

pens

whe

n ex

pose

d

84

SKIN

CO

NTA

CT

SHO

RT T

ERM

EXP

OSU

RE i

rrita

tion

LON

G T

ERM

EXP

OSU

RE s

ame

as e

ffect

s re

port

ed in

sho

rt t

erm

exp

osur

eEY

E CO

NTA

CThellip

ING

ESTI

ON

hellip

CARC

INO

GEN

STA

TUS

OSH

A N

NTP

NIA

RC N

SECT

ION

4 F

IRST

AID

MEA

SUR

ESIN

HAL

ATIO

Nhellip

SKIN

CO

NTA

CThellip

EYE

CON

TACT

hellipIN

GES

TIO

Nhellip

SECT

ION

5 F

IRE

FIG

HTI

NG

MEA

SUR

ES

Wha

t sho

uld

you

do if

exp

osed

Doe

s it

caus

e ca

ncer

85

SECT

ION

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

Timeline for NASA University Student Launch Initiative (Dates are subject to change)

August 2015 7 Request for Proposal (RFP) goes out to all teams

September 201511 Electronic copy of completed proposal due to project office by 5 pm CDT to

Ian Bryant (Jacobs ESSSA Group) ianlbryantnasagov

Katie Wallace katievwallacenasagov

Julie Clift juliedcliftnasagov

October 2015 2 Awarded proposals announced 7 Kickoff and PDR QampA 23 Team web presence established

November 2015 6 Preliminary Design Review (PDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 9-20 PDR video teleconferences

December 2015 4 CDR QampA

January 201615 Critical Design Review (CDR) reports presentation slides and flysheet posted on the team

Website by 800 am Central Time 19-29 CDR video teleconferences

February 20163 FRR QampA

March 2016 14 Flight Readiness Review (FRR) reports presentation slides and flysheet posted to team Website

by 800 am Central Time 17-30 FRR video teleconferences

April 201613 Teams travel to Huntsville AL 13 Launch Readiness Reviews (LRR) 14 LRRrsquos and safety briefing 15 Rocket Fair and Tours of MSFC 16 Launch Day 17 Backup launch day 29 Post-Launch Assessment Review (PLAR) posted on the team Website by 800 am Central Time

May 2016Winning team announced 11

1

Acronym Dictionary

AGL=Above Ground Level

APCP=Ammonium Perchlorate Composite Propellant

CDR=Critical Design Review

CC=Centennial Challenges

CG=Center of Gravity

CP=Center of Pressure

EIT=Electronics and Information Technology

FAA=Federal Aviation Administration

FN=Foreign National

FRR=Flight Readiness Review

HEO=Human Exploration and Operations

LCO=Launch Control Officer

LRR=Launch Readiness Review

MAV=Mars Ascent Vehicle

MSDS=Material Safety Data Sheet

MSFC=Marshall Space Flight Center

NAR=National Association of Rocketry

PDR=Preliminary Design Review

PLAR=Post Launch Assessment Review

PPE=Personal Protective Equipment

RFP=Request for Proposal

RSO=Range Safety Officer

USLI=University Student Launch Initiative

SME=Subject Matter Expert

SOW=Statement of Work

STEM=Science Technology Engineering and Mathematics

TRA=Tripoli Rocketry Association

2

ProposalStatement of Work for Colleges UniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement

of Work (SOW)

1 Project Name NASA University Student Launch Initiative for colleges and universities

2 Governing Office NASA Marshall Space Flight Center Academic Affairs Office

3 Period of Performance Eight (8) calendar months

4 IntroductionThe NASA University Student Launch Initiative (USLI) is a research-based competitive and experiential

exploration project that provides relevant and cost effective research and development Additionally NASA

University Student Launch Initiative connects learners educators and communities in NASA-unique

opportunities that align with STEM Challenges under the NASA Education Science Technology Engineering

and Mathematics (STEM) Engagement line of business NASArsquos missions discoveries and assets provide

opportunities for individuals that do not exist elsewhere The project involves reaching a broach audience of

colleges and universities across the nation in an 8-month commitment to design build launch and fly a

payload(s) and vehicle components that support NASA research on high-power rockets to an altitude of

5280 feet above ground level (AGL) The challenge is based on team selection of multiple options There is

a Student Launch option that consists of 7 different experiments and a Centennial Challenge (CC) option

that consists of designing and building a Mars Ascent Vehicle (MAV) Supported by the Office of Education

Human Exploration and Operations (HEO) Mission Directorate Centennial Challenges Office and

commercial industry USLI is a unique NASA-specific opportunity to provide resources and experiences thatis built around a mission not textbook knowledge

After a competitive proposal selection process teams participate in a series of design reviews that are

submitted to NASA via a team-developed website These reviews mirror the NASA engineering design

lifecycle providing a NASA-unique experience that prepares individuals for the HEO workforce Teams must

successfully complete a Preliminary Design Review (PDR) Critical Design Review (CDR) Flight Readiness

Review (FRR) Launch Readiness Review (LRR) that includes safety briefings and an analysis of vehicle

systems ground support equipment and flight data Each team must pass a review in order to move to a

subsequent review Teams will present their PDR CDR and FRR to a review panel of scientists engineers

technicians and educators via video teleconference Review panel members the Range Safety Officer

(RSO) and Subject Matter Experts (SME) provide feedback and ask questions in order to increase the

fidelity between the USLI and research needs and will score each team according to a standard scoring

rubric The partnership of teams and NASA is win-win which not only benefits from the research conducted

by the teams but also prepares a potential future workforce familiar with the NASA Engineering Design

Lifecycle

College and university teams must successfully complete the requirements of Tasks 1 or 2 and are eligible

for awards through Student Launch Any team who wishes to incorporate additional research through the use

of a separate payload may do so The team must provide documentation in all reports and reviews oncomponents and systems outside of what is required for the project The Centennial Challenges Office will

award prizes to college university and non-academic teams for successful demonstration of the MAV (see

CC supplemental handbook) The USLI awards listed at the end of this handbook will only be given to teams

from an academic institution

4

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

NAS

A Pr

ojec

t Life

Cyc

le

Char

les P

ierc

eDe

puty

Chi

ef S

pace

craf

t amp A

uxili

ary

Prop

ulsio

n Sy

stem

s Bra

nch

NAS

A -M

arsh

all S

pace

Flig

ht C

ente

r

39

Topi

cs

bullPu

rpos

e O

bjec

tive

bullPr

ojec

t Life

Cyc

lebull

Syst

em R

equi

rem

ents

Rev

iew

(NA

to N

ASA

Stud

ent L

aunc

h)bull

Prel

imin

ary

Desig

nbull

Criti

cal (

Fina

l) De

sign

bullFl

ight

Rea

dine

ss

40

Purp

ose

Obj

ectiv

es

of th

e N

ASA

Proj

ect L

ife C

ycle

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an fo

r the

des

ign

bui

ld v

erifi

catio

n fl

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erat

ions

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osal

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esire

d sy

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etw

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and

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ndashPl

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eliv

erab

les

ndashFi

delit

yndash

Tim

ing

41

Typi

cal N

ASA

Proj

ect L

ife C

ycle

Refe

renc

e N

PR 71

205

D F

igur

e 2-

4 ldquo

The

NAS

A Pr

ojec

t Life

Cyc

lerdquo

42

Stud

ent L

aunc

h Pr

ojec

ts L

ife C

ycle

Phas

e A

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e B

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e C

Phas

e D

Phas

e E

Phas

e F

Acqu

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on amp

Pr

elim

inar

y De

sign

Fina

l Des

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Fabr

icat

ion

amp

Ope

ratio

ns amp

Di

spos

alRe

quire

men

tsLa

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Sust

ainm

ent

Auth

ority

to P

roce

edSR

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RCD

RFR

R Laun

chbull

ATP

(Aut

horit

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Proc

eed)

ndashFu

ndin

g is

appl

ied

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e co

ntra

cte

ffort

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wor

k per

form

ance

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n be

gin

bullSR

R (S

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m R

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iew

) ndashTo

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vel R

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d in

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stem

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ts S

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m R

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ewed

and

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iven

to p

roce

ed in

to

Prel

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ary

Desig

n T

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h Pr

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ep

bullPD

R (P

relim

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y Des

ign

Revi

ew) ndash

Prel

imin

ary

Desig

n is

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ewed

and

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horit

y is g

iven

to

proc

eed

into

Fin

al D

esig

nbull

CDR

(Crit

ical

Des

ign

Revi

ew) ndash

Fina

l Des

ign

is re

view

ed a

nd a

utho

rity i

s giv

en to

pro

ceed

to

build

the

syst

em

bullFR

R (F

light

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dine

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As-b

uilt

desig

n an

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ata

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ewed

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give

n fo

r Lau

nch

43

Prel

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ary

Desi

gn R

evie

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Obj

ectiv

endash

Prov

e th

e fe

asib

ility

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uild

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ch th

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at a

ll sy

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will

be

met

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Rece

ive

auth

ority

to p

roce

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the

Fina

l Des

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Phas

ebull

Typi

cal P

rodu

cts (

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cle

and

Payl

oad)

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hedu

le (d

esig

n b

uild

tes

t)ndash

Cost

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get S

tate

men

tndash

Prel

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n Pr

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of O

pera

tions

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Inte

rfac

es (w

ithin

the

syst

em an

d ex

tern

al to

the

syst

em)

ndashTe

st a

nd V

erifi

catio

n Pl

anndash

Gro

und

Supp

ort E

quip

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t Des

igns

Ide

ntifi

catio

nndash

Safe

ty F

eatu

res

44

Criti

cal D

esig

n Re

view

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bjec

tive

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mpl

ete

the

final

des

ign

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e ro

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ceiv

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Verif

icat

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e

bullTy

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l Pro

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hicl

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ured

to re

flect

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final

des

ign)

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port

and

dis

cuss

com

plet

ed te

sts

ndashPr

oced

ures

and

Che

cklis

ts

45

Flig

ht R

eadi

ness

Rev

iew

bullO

bjec

tive

ndashPr

ove

that

the

Rock

etP

aylo

ad Sy

stem

has

bee

n fu

lly b

uilt

test

ed a

nd v

erifi

ed

to m

eet t

he sy

stem

requ

irem

ents

ndashPr

ove

that

all

syst

em re

quire

men

ts h

ave

been

or w

ill b

e m

etndash

Rece

ive

auth

ority

to La

unch

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

Sche

dule

ndashCo

st S

tate

men

tndash

Desig

n O

verv

iew

bullKe

y com

pone

nts

bullKe

y dra

win

gs an

d la

yout

sbull

Traj

ecto

ry an

d ot

her k

ey a

naly

ses

bullM

ass S

tate

men

t bull

Rem

aini

ng R

isks

ndashM

issio

n Pr

ofile

ndash

Pres

enta

tion

and

anal

ysis

of te

st d

ata

ndashSy

stem

Req

uire

men

ts V

erifi

catio

nndash

Gro

und

Supp

ort E

quip

men

t ndash

Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Per

sonn

el

expo

sure

to

high

vol

tage

Con

tact

with

en

ergi

zed

lam

p ba

nk c

ircu

its

Dea

th o

r se

vere

pe

rson

nel i

njur

y 1C

1

D

urin

g te

st o

pera

tion

lam

p ba

nks

circ

uits

will

be

ener

gize

d on

ly w

hen

no

pers

onne

l are

insi

de c

ham

ber

2

D

oor

to c

ham

ber

wil

l be

clos

ed

prio

r to

ene

rgiz

ing

circ

uits

3

T

S30

0 ac

cess

con

trol

s ar

e in

pl

ace

for

the

test

1

304-

TC

P-0

16 S

ectio

n 3

13

requ

ires

di

sabl

ing

heat

er e

lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r 2

P

er 3

04-T

CP

-016

tes

ts w

ill o

nly

be

perf

orm

ed u

nder

per

sona

l dir

ectio

n of

Tes

t E

ngin

eer

3

Acc

ess

cont

rols

for

this

test

are

in

clud

ed in

304

-TC

P-0

16 T

hese

incl

ude

o

L

ower

Eas

t Tes

t Are

a G

ate

6 a

nd T

urn

C6

Lig

ht to

RE

D

o

Low

er E

ast T

est A

rea

Gat

e 7

and

Tur

n C

7 L

ight

to R

ED

o

L

ower

Eas

t Tes

t Are

a G

ate

8 a

nd T

urn

C8

Lig

ht to

RE

D

o

Ver

ify

all G

over

nmen

t spo

nsor

ed v

ehic

les

are

clea

r of

the

area

o

V

erif

y al

l non

-Gov

ernm

ent s

pons

ored

ve

hicl

es a

re c

lear

of

the

area

o

M

ake

the

follo

win

g an

noun

cem

ent

ldquoAtte

ntio

n al

l per

sonn

el t

est o

pera

tions

ar

e ab

out t

o be

gin

at T

S30

0 T

he a

rea

is

clea

red

for

the

Des

igna

ted

Cre

w O

nly

and

wil

l rem

ain

until

fur

ther

not

ice

rdquo (R

EP

EA

T)

1E

Per

sonn

el

expo

sure

to a

n ox

ygen

de

fici

ent

envi

ronm

ent

Ent

ry in

to 1

2 ft

ch

ambe

r w

ith

unkn

own

atm

osph

ere

Dea

th o

r se

vere

pe

rson

nel i

njur

y 1C

1

O

xyge

n m

onito

rs a

re s

tatio

ned

insi

de c

ham

ber

and

cham

ber

entr

yway

2

C

ham

ber

air

vent

ilat

or o

pera

ted

afte

r ea

ch p

anel

test

to v

ent c

ham

ber

1

304-

TC

P-0

16 r

equi

res

inst

alla

tion

of

the

Tes

t Art

icle

usi

ng ldquo

Tes

t Pan

el

Inst

allR

emov

al P

roce

dure

rdquo T

his

proc

edur

e re

quir

es u

se o

f a

port

able

O2

mon

itor

in th

e se

ctio

n en

title

d ldquoP

ost T

est A

ctiv

ities

and

Tes

t P

anel

Rem

oval

rdquo S

tep

1

2

304-

TC

P-0

16 S

ectio

n 3

122

req

uire

s C

ham

ber

Ven

t Sys

tem

to r

un f

or 3

+ M

inut

es

prio

r to

ent

erin

g th

e ch

ambe

r to

rem

ove

the

pane

l

1E

60

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

3

Atte

ndan

t will

be

post

ed o

utsi

de

cham

ber

to m

onit

or in

-cha

mbe

r ac

tivi

ties

fa

cili

tate

eva

cuat

ion

or r

escu

e if

req

uire

d

and

to r

estr

ict a

cces

s to

una

utho

rize

d pe

rson

nel

4

Fir

e D

ept

to b

e no

tifie

d th

at

conf

ined

spa

ce e

ntri

es a

re b

eing

mad

e

3

ldquoTes

t Pan

el I

nsta

llR

emov

al

Pro

cedu

rerdquo

pag

e 1

req

uire

s th

e us

e of

exi

stin

g M

ET

TS

con

fine

d sp

ace

entr

y pr

oced

ures

w

hich

incl

udes

req

uire

men

t for

an

atte

ndan

t w

hen

ente

ring

the

12 f

t vac

uum

cha

mbe

r re

fere

nce

Con

fine

d S

pace

Per

mit

0298

4

ldquoT

est P

anel

Ins

tall

Rem

oval

P

roce

dure

rdquo p

age

1 r

equi

res

the

use

of e

xist

ing

ME

TT

S c

onfi

ned

spac

e en

try

proc

edur

es

whi

ch in

clud

es r

equi

rem

ent t

o no

tify

the

Fir

e D

ept

prio

r to

ent

erin

g th

e 12

ft v

acuu

m

cham

ber

Ref

eren

ce C

onfi

ned

Spa

ce P

erm

it

0298

Per

sonn

el

expo

sure

to

lam

p th

erm

al

ener

gy

P

roxi

mit

y to

la

mps

whi

le

ener

gize

d

Acc

iden

tal

cont

act w

ith

lam

p or

ca

libra

tion

plat

e w

hile

out

Per

sonn

el b

urns

re

quir

ing

med

ical

tr

eatm

ent

3C

1

Dur

ing

test

ope

rati

on l

amp

bank

s ci

rcui

ts w

ill b

e en

ergi

zed

only

whe

n no

pe

rson

nel a

re in

side

cha

mbe

r

2

Doo

r to

cha

mbe

r w

ill c

lose

d pr

ior

to e

nerg

izin

g ci

rcui

ts

3

De s

igna

ted

pers

onne

l will

wea

r

leat

her

glov

es to

han

dle

calib

ratio

n pl

ate

if r

equi

red

1

304-

TC

P-0

16 S

ectio

n 3

13

requ

ires

di

sabl

ing

heat

er e

lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r

2

Per

304

-TC

P-0

16 t

ests

wil

l onl

y be

pe

rfor

med

und

er p

erso

nal d

irec

tion

of T

est

Eng

inee

r 3

30

4-T

CP

-16

Sec

tion

14

Haz

ards

and

C

ontr

ols

req

uire

s in

sula

ted

glov

es a

s re

quir

ed

if h

ot it

ems

need

to b

e ha

ndle

d

3E

61

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Fai

lure

of

pres

sure

sy

stem

s

Ove

r-pr

essu

riza

tion

Per

sonn

el in

jury

Equ

ipm

ent

dam

age

1C

1

TS

300

faci

lity

pres

sure

sys

tem

s ar

e ce

rtif

ied

2

P

er E

T10

test

eng

inee

r h

igh

puri

ty a

ir s

yste

m w

ill b

e us

ed a

t lt 1

50

psig

ope

rati

ng p

ress

ure

ther

efor

e ce

rtif

icat

ion

not r

equi

red

3

A

ll n

on-c

erti

fied

test

equ

ipm

ent i

s pn

eum

atic

ally

pre

ssur

e te

sted

to 1

50

of

Max

imum

All

owab

le W

orki

ng P

ress

ure

(MA

WP

)

1

Per

the

MS

FC

Pre

ssur

e S

yste

ms

Rep

ortin

g T

ool (

PS

RT

) f

acili

ty s

yste

ms

have

be

en r

ecer

tifie

d un

der

TL

WT

-CE

RT

-10-

TS

300-

RR

2002

unt

il 3

320

20 T

he

cert

ific

atio

n in

clud

es G

aseo

us H

eliu

m G

aseo

us

Hyd

roge

n G

aseo

us N

itro

gen

Hig

h Pu

rity

Air

L

iqui

d H

ydro

gen

and

Liq

uid

Nitr

ogen

sys

tem

s

2

304-

TC

P-0

16 S

tep

21

14 r

equi

res

HO

R-1

2-12

8 2

nd S

tage

HP

Air

HO

R t

o be

L

oade

d to

75p

sig

3

S

ee P

ress

ure

Tes

t Rep

ort P

TR

-001

455

(App

endi

x A

) A

ll no

n-ce

rtif

ied

equi

pmen

t has

a

min

imum

fac

tor

of s

afet

y of

41

1E

Foa

m p

anel

ca

tche

s fi

re

duri

ng te

stin

g

Tes

t req

uire

s hi

gh

heat

wit

h po

ssib

ility

of

pane

l bu

rnin

g

Rel

ease

of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

ion

requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

hed

Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

s so

ver

y lit

tle

or n

o re

sidu

al g

asse

s or

vap

ors

rem

ain

1

A m

inim

um v

enti

lati

on o

f th

e ch

ambe

r sh

ould

the

foam

pan

el b

urn

duri

ng o

r af

ter

test

ing

has

been

est

ablis

hed

by p

roce

dure

304

-T

CP

-016

whi

ch r

equi

res

the

min

imum

10

min

ute

vent

ilatio

n be

fore

per

sonn

el a

re a

llow

ed

to e

nter

Add

ition

ally

if

any

abno

rmal

ities

are

ob

serv

ed th

e In

dust

rial

Hea

lth r

epre

sent

ativ

e w

ill b

e ca

lled

to p

erfo

rm a

dditi

onal

air

sa

mpl

ing

befo

re p

erso

nnel

ent

ry

1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

Acronym Dictionary

AGL=Above Ground Level

APCP=Ammonium Perchlorate Composite Propellant

CDR=Critical Design Review

CC=Centennial Challenges

CG=Center of Gravity

CP=Center of Pressure

EIT=Electronics and Information Technology

FAA=Federal Aviation Administration

FN=Foreign National

FRR=Flight Readiness Review

HEO=Human Exploration and Operations

LCO=Launch Control Officer

LRR=Launch Readiness Review

MAV=Mars Ascent Vehicle

MSDS=Material Safety Data Sheet

MSFC=Marshall Space Flight Center

NAR=National Association of Rocketry

PDR=Preliminary Design Review

PLAR=Post Launch Assessment Review

PPE=Personal Protective Equipment

RFP=Request for Proposal

RSO=Range Safety Officer

USLI=University Student Launch Initiative

SME=Subject Matter Expert

SOW=Statement of Work

STEM=Science Technology Engineering and Mathematics

TRA=Tripoli Rocketry Association

2

ProposalStatement of Work for Colleges UniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement

of Work (SOW)

1 Project Name NASA University Student Launch Initiative for colleges and universities

2 Governing Office NASA Marshall Space Flight Center Academic Affairs Office

3 Period of Performance Eight (8) calendar months

4 IntroductionThe NASA University Student Launch Initiative (USLI) is a research-based competitive and experiential

exploration project that provides relevant and cost effective research and development Additionally NASA

University Student Launch Initiative connects learners educators and communities in NASA-unique

opportunities that align with STEM Challenges under the NASA Education Science Technology Engineering

and Mathematics (STEM) Engagement line of business NASArsquos missions discoveries and assets provide

opportunities for individuals that do not exist elsewhere The project involves reaching a broach audience of

colleges and universities across the nation in an 8-month commitment to design build launch and fly a

payload(s) and vehicle components that support NASA research on high-power rockets to an altitude of

5280 feet above ground level (AGL) The challenge is based on team selection of multiple options There is

a Student Launch option that consists of 7 different experiments and a Centennial Challenge (CC) option

that consists of designing and building a Mars Ascent Vehicle (MAV) Supported by the Office of Education

Human Exploration and Operations (HEO) Mission Directorate Centennial Challenges Office and

commercial industry USLI is a unique NASA-specific opportunity to provide resources and experiences thatis built around a mission not textbook knowledge

After a competitive proposal selection process teams participate in a series of design reviews that are

submitted to NASA via a team-developed website These reviews mirror the NASA engineering design

lifecycle providing a NASA-unique experience that prepares individuals for the HEO workforce Teams must

successfully complete a Preliminary Design Review (PDR) Critical Design Review (CDR) Flight Readiness

Review (FRR) Launch Readiness Review (LRR) that includes safety briefings and an analysis of vehicle

systems ground support equipment and flight data Each team must pass a review in order to move to a

subsequent review Teams will present their PDR CDR and FRR to a review panel of scientists engineers

technicians and educators via video teleconference Review panel members the Range Safety Officer

(RSO) and Subject Matter Experts (SME) provide feedback and ask questions in order to increase the

fidelity between the USLI and research needs and will score each team according to a standard scoring

rubric The partnership of teams and NASA is win-win which not only benefits from the research conducted

by the teams but also prepares a potential future workforce familiar with the NASA Engineering Design

Lifecycle

College and university teams must successfully complete the requirements of Tasks 1 or 2 and are eligible

for awards through Student Launch Any team who wishes to incorporate additional research through the use

of a separate payload may do so The team must provide documentation in all reports and reviews oncomponents and systems outside of what is required for the project The Centennial Challenges Office will

award prizes to college university and non-academic teams for successful demonstration of the MAV (see

CC supplemental handbook) The USLI awards listed at the end of this handbook will only be given to teams

from an academic institution

4

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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edur

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s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

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exa

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e of

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azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

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of w

hich

pla

y in

to

how

we

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e it

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ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

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ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

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re-

RA

C

Mit

igat

ion

Ver

ific

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T

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Tes

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304

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Add

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1E

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Und

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By

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MS

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nviro

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63

Wha

t is

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SD

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A

Mat

eria

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Dat

a S

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(M

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man

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tend

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preh

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with

or h

andl

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is

chem

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64

Wha

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M

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Srsquos

do

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y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

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ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

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MET

HYL

ACE

TON

E 3

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TAN

ON

E M

EK

SCO

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P reg

BRA

ND

SO

LVEN

T

3 (3

M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

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RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

ress

ion

PHYS

ICAL

HAZ

ARD

S F

lam

mab

le li

quid

and

vap

or V

apor

may

cau

se fl

ash

fire

Goo

d in

fo fo

rla

belin

g co

ntai

ners

23

0

POTE

NTI

AL H

EALT

H E

FFEC

TS

INH

ALAT

ION

SH

ORT

TER

M E

XPO

SURE

irr

itatio

n n

ause

a v

omiti

ng d

iffic

ulty

bre

athi

ng

Wha

t hap

pens

whe

n ex

pose

d

84

SKIN

CO

NTA

CT

SHO

RT T

ERM

EXP

OSU

RE i

rrita

tion

LON

G T

ERM

EXP

OSU

RE s

ame

as e

ffect

s re

port

ed in

sho

rt t

erm

exp

osur

eEY

E CO

NTA

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ESTI

ON

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INO

GEN

STA

TUS

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A N

NTP

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RC N

SECT

ION

4 F

IRST

AID

MEA

SUR

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HAL

ATIO

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SKIN

CO

NTA

CThellip

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TACT

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GES

TIO

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SECT

ION

5 F

IRE

FIG

HTI

NG

MEA

SUR

ES

Wha

t sho

uld

you

do if

exp

osed

Doe

s it

caus

e ca

ncer

85

SECT

ION

6 A

CCID

ENTA

L R

ELEA

SE M

EASU

RES

AIR

RELE

ASE

Redu

ce v

apor

s w

ith w

ater

spr

aySO

IL R

ELEA

SE

Dig

hol

ding

are

a su

ch a

s la

goon

pon

d or

pit

for

cont

ainm

ent

Abs

orb

with

hellip

SECT

ION

7 H

AND

LIN

G A

ND

STO

RAG

E

Stor

e an

d ha

ndle

in a

ccor

danc

e hellip

SECT

ION

8 E

XPO

SUR

E CO

NTR

OLS

PER

SON

AL P

RO

TECT

ION

EXPO

SURE

LIM

ITS

MET

HYL

ETH

YL K

ETO

NE

MET

HYL

ETH

YL K

ETO

NE

200

ppm

(59

0 m

gm

3) O

SHA

TWA

300

ppm

(88

5 m

gm

3) O

SHA

STEL

200

ppm

(59

0 m

gm

3) A

CGIH

TW

A30

0 pp

m (

885

mg

m3)

ACG

IH S

TEL

8 hr

avg

15 m

in a

vg

86

SECT

ION

9 P

HYS

ICAL

AN

D C

HEM

ICAL

PR

OPE

RTIE

S

COLO

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olor

less

PHYS

ICAL

FO

RM l

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inty

sw

eet o

dor

MO

LECU

LAR

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T 7

212

MO

LECU

LAR

FORM

ULA

C-H

3-C-

H2-

C-O

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ILIN

G P

OIN

T 1

76 F

(80

C)

FREE

ZIN

G P

OIN

T -1

23 F

(-8

6 C)

VAPO

R PR

ESSU

RE 1

00 m

mH

g

25

CVA

POR

DEN

SITY

(ai

r =

1)

25

SPEC

IFIC

GRA

VITY

(w

ater

= 1

) 0

805

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ATER

SO

LUBI

LITY

27

5PH

No

data

ava

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eVO

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LITY

No

data

ava

ilabl

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DO

R TH

RESH

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02

5-10

ppm

EVAP

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TIO

N R

ATE

27

(et

her =

1)

VISC

OSI

TY 0

40

cP

25 C

SOLV

ENT

SOLU

BILI

TY a

lcoh

ol e

ther

ben

zene

ace

tone

oils

sol

vent

s

MYT

H i

f it

smel

ls b

ad it

is h

arm

ful

if it

smel

ls g

ood

it is

saf

e

MEK

vap

or is

hea

vier

than

air

MEK

liqu

id w

ill fl

oat o

n st

agna

nt w

ater

Not

ver

y so

lubl

e in

wat

er

Will

like

ly s

mel

l MEK

bef

ore

bein

g ov

erex

pose

d

Goe

s to

vap

or e

asy

87

SECT

ION

10

STA

BILI

TY A

ND

REA

CTIV

ITY

SECT

ION

11

TO

XICO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

12

ECO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

13

DIS

POSA

L CO

NSI

DER

ATIO

NS

SECT

ION

14

TR

ANSP

ORT

INFO

RM

ATIO

N

SECT

ION

15

REG

ULA

TOR

Y IN

FOR

MAT

ION

SECT

ION

16

OTH

ER IN

FOR

MAT

ION

MSD

Srsquos

have

an

abun

danc

e of

in

form

atio

n us

eful

in

man

y di

ffer

ent

aspe

cts

88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

ProposalStatement of Work for Colleges UniversitiesNon-Academic Teams

Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement

of Work (SOW)

1 Project Name NASA University Student Launch Initiative for colleges and universities

2 Governing Office NASA Marshall Space Flight Center Academic Affairs Office

3 Period of Performance Eight (8) calendar months

4 IntroductionThe NASA University Student Launch Initiative (USLI) is a research-based competitive and experiential

exploration project that provides relevant and cost effective research and development Additionally NASA

University Student Launch Initiative connects learners educators and communities in NASA-unique

opportunities that align with STEM Challenges under the NASA Education Science Technology Engineering

and Mathematics (STEM) Engagement line of business NASArsquos missions discoveries and assets provide

opportunities for individuals that do not exist elsewhere The project involves reaching a broach audience of

colleges and universities across the nation in an 8-month commitment to design build launch and fly a

payload(s) and vehicle components that support NASA research on high-power rockets to an altitude of

5280 feet above ground level (AGL) The challenge is based on team selection of multiple options There is

a Student Launch option that consists of 7 different experiments and a Centennial Challenge (CC) option

that consists of designing and building a Mars Ascent Vehicle (MAV) Supported by the Office of Education

Human Exploration and Operations (HEO) Mission Directorate Centennial Challenges Office and

commercial industry USLI is a unique NASA-specific opportunity to provide resources and experiences thatis built around a mission not textbook knowledge

After a competitive proposal selection process teams participate in a series of design reviews that are

submitted to NASA via a team-developed website These reviews mirror the NASA engineering design

lifecycle providing a NASA-unique experience that prepares individuals for the HEO workforce Teams must

successfully complete a Preliminary Design Review (PDR) Critical Design Review (CDR) Flight Readiness

Review (FRR) Launch Readiness Review (LRR) that includes safety briefings and an analysis of vehicle

systems ground support equipment and flight data Each team must pass a review in order to move to a

subsequent review Teams will present their PDR CDR and FRR to a review panel of scientists engineers

technicians and educators via video teleconference Review panel members the Range Safety Officer

(RSO) and Subject Matter Experts (SME) provide feedback and ask questions in order to increase the

fidelity between the USLI and research needs and will score each team according to a standard scoring

rubric The partnership of teams and NASA is win-win which not only benefits from the research conducted

by the teams but also prepares a potential future workforce familiar with the NASA Engineering Design

Lifecycle

College and university teams must successfully complete the requirements of Tasks 1 or 2 and are eligible

for awards through Student Launch Any team who wishes to incorporate additional research through the use

of a separate payload may do so The team must provide documentation in all reports and reviews oncomponents and systems outside of what is required for the project The Centennial Challenges Office will

award prizes to college university and non-academic teams for successful demonstration of the MAV (see

CC supplemental handbook) The USLI awards listed at the end of this handbook will only be given to teams

from an academic institution

4

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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iven

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proc

eed

into

Fin

al D

esig

nbull

CDR

(Crit

ical

Des

ign

Revi

ew) ndash

Fina

l Des

ign

is re

view

ed a

nd a

utho

rity i

s giv

en to

pro

ceed

to

build

the

syst

em

bullFR

R (F

light

Rea

dine

ss R

evie

w) ndash

As-b

uilt

desig

n an

d te

st d

ata

are

revi

ewed

and

aut

horit

y is

give

n fo

r Lau

nch

43

Prel

imin

ary

Desi

gn R

evie

wbull

Obj

ectiv

endash

Prov

e th

e fe

asib

ility

to b

uild

and

laun

ch th

e ro

cket

pay

load

des

ign

ndash

Prov

e th

at a

ll sy

stem

requ

irem

ents

will

be

met

ndash

Rece

ive

auth

ority

to p

roce

ed to

the

Fina

l Des

ign

Phas

ebull

Typi

cal P

rodu

cts (

Vehi

cle

and

Payl

oad)

ndashSc

hedu

le (d

esig

n b

uild

tes

t)ndash

Cost

Bud

get S

tate

men

tndash

Prel

imin

ary

Desig

n Di

scus

sion

bullDr

awin

gs s

ketc

hes

bullId

entif

icatio

n an

d di

scus

sion

of co

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nent

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Anal

yses

(suc

h as

Veh

icle

Traj

ecto

ry P

redi

ctio

ns)

bullRi

sks

bullM

ass S

tate

men

t and

Mas

s Mar

gin

ndashM

issio

n Pr

ofile

(Con

cept

of O

pera

tions

)ndash

Inte

rfac

es (w

ithin

the

syst

em an

d ex

tern

al to

the

syst

em)

ndashTe

st a

nd V

erifi

catio

n Pl

anndash

Gro

und

Supp

ort E

quip

men

t Des

igns

Ide

ntifi

catio

nndash

Safe

ty F

eatu

res

44

Criti

cal D

esig

n Re

view

bullO

bjec

tive

ndashCo

mpl

ete

the

final

des

ign

of th

e ro

cket

pay

load

sys

tem

ndashRe

ceiv

e au

thor

ity to

pro

ceed

into

Fab

ricat

ion

and

Verif

icat

ion

phas

e

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

PDR

Deliv

erab

les

(mat

ured

to re

flect

the

final

des

ign)

ndashRe

port

and

dis

cuss

com

plet

ed te

sts

ndashPr

oced

ures

and

Che

cklis

ts

45

Flig

ht R

eadi

ness

Rev

iew

bullO

bjec

tive

ndashPr

ove

that

the

Rock

etP

aylo

ad Sy

stem

has

bee

n fu

lly b

uilt

test

ed a

nd v

erifi

ed

to m

eet t

he sy

stem

requ

irem

ents

ndashPr

ove

that

all

syst

em re

quire

men

ts h

ave

been

or w

ill b

e m

etndash

Rece

ive

auth

ority

to La

unch

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

Sche

dule

ndashCo

st S

tate

men

tndash

Desig

n O

verv

iew

bullKe

y com

pone

nts

bullKe

y dra

win

gs an

d la

yout

sbull

Traj

ecto

ry an

d ot

her k

ey a

naly

ses

bullM

ass S

tate

men

t bull

Rem

aini

ng R

isks

ndashM

issio

n Pr

ofile

ndash

Pres

enta

tion

and

anal

ysis

of te

st d

ata

ndashSy

stem

Req

uire

men

ts V

erifi

catio

nndash

Gro

und

Supp

ort E

quip

men

t ndash

Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

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E

ffec

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Per

sonn

el b

urns

re

quir

ing

med

ical

tr

eatm

ent

3C

1

Dur

ing

test

ope

rati

on l

amp

bank

s ci

rcui

ts w

ill b

e en

ergi

zed

only

whe

n no

pe

rson

nel a

re in

side

cha

mbe

r

2

Doo

r to

cha

mbe

r w

ill c

lose

d pr

ior

to e

nerg

izin

g ci

rcui

ts

3

De s

igna

ted

pers

onne

l will

wea

r

leat

her

glov

es to

han

dle

calib

ratio

n pl

ate

if r

equi

red

1

304-

TC

P-0

16 S

ectio

n 3

13

requ

ires

di

sabl

ing

heat

er e

lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r

2

Per

304

-TC

P-0

16 t

ests

wil

l onl

y be

pe

rfor

med

und

er p

erso

nal d

irec

tion

of T

est

Eng

inee

r 3

30

4-T

CP

-16

Sec

tion

14

Haz

ards

and

C

ontr

ols

req

uire

s in

sula

ted

glov

es a

s re

quir

ed

if h

ot it

ems

need

to b

e ha

ndle

d

3E

61

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Fai

lure

of

pres

sure

sy

stem

s

Ove

r-pr

essu

riza

tion

Per

sonn

el in

jury

Equ

ipm

ent

dam

age

1C

1

TS

300

faci

lity

pres

sure

sys

tem

s ar

e ce

rtif

ied

2

P

er E

T10

test

eng

inee

r h

igh

puri

ty a

ir s

yste

m w

ill b

e us

ed a

t lt 1

50

psig

ope

rati

ng p

ress

ure

ther

efor

e ce

rtif

icat

ion

not r

equi

red

3

A

ll n

on-c

erti

fied

test

equ

ipm

ent i

s pn

eum

atic

ally

pre

ssur

e te

sted

to 1

50

of

Max

imum

All

owab

le W

orki

ng P

ress

ure

(MA

WP

)

1

Per

the

MS

FC

Pre

ssur

e S

yste

ms

Rep

ortin

g T

ool (

PS

RT

) f

acili

ty s

yste

ms

have

be

en r

ecer

tifie

d un

der

TL

WT

-CE

RT

-10-

TS

300-

RR

2002

unt

il 3

320

20 T

he

cert

ific

atio

n in

clud

es G

aseo

us H

eliu

m G

aseo

us

Hyd

roge

n G

aseo

us N

itro

gen

Hig

h Pu

rity

Air

L

iqui

d H

ydro

gen

and

Liq

uid

Nitr

ogen

sys

tem

s

2

304-

TC

P-0

16 S

tep

21

14 r

equi

res

HO

R-1

2-12

8 2

nd S

tage

HP

Air

HO

R t

o be

L

oade

d to

75p

sig

3

S

ee P

ress

ure

Tes

t Rep

ort P

TR

-001

455

(App

endi

x A

) A

ll no

n-ce

rtif

ied

equi

pmen

t has

a

min

imum

fac

tor

of s

afet

y of

41

1E

Foa

m p

anel

ca

tche

s fi

re

duri

ng te

stin

g

Tes

t req

uire

s hi

gh

heat

wit

h po

ssib

ility

of

pane

l bu

rnin

g

Rel

ease

of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

ion

requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

hed

Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

s so

ver

y lit

tle

or n

o re

sidu

al g

asse

s or

vap

ors

rem

ain

1

A m

inim

um v

enti

lati

on o

f th

e ch

ambe

r sh

ould

the

foam

pan

el b

urn

duri

ng o

r af

ter

test

ing

has

been

est

ablis

hed

by p

roce

dure

304

-T

CP

-016

whi

ch r

equi

res

the

min

imum

10

min

ute

vent

ilatio

n be

fore

per

sonn

el a

re a

llow

ed

to e

nter

Add

ition

ally

if

any

abno

rmal

ities

are

ob

serv

ed th

e In

dust

rial

Hea

lth r

epre

sent

ativ

e w

ill b

e ca

lled

to p

erfo

rm a

dditi

onal

air

sa

mpl

ing

befo

re p

erso

nnel

ent

ry

1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

-3RT

ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

NE

MET

HYL

ACE

TON

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TAN

ON

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EK

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BRA

ND

SO

LVEN

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M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

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RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement

of Work (SOW)

1 Project Name NASA University Student Launch Initiative for colleges and universities

2 Governing Office NASA Marshall Space Flight Center Academic Affairs Office

3 Period of Performance Eight (8) calendar months

4 IntroductionThe NASA University Student Launch Initiative (USLI) is a research-based competitive and experiential

exploration project that provides relevant and cost effective research and development Additionally NASA

University Student Launch Initiative connects learners educators and communities in NASA-unique

opportunities that align with STEM Challenges under the NASA Education Science Technology Engineering

and Mathematics (STEM) Engagement line of business NASArsquos missions discoveries and assets provide

opportunities for individuals that do not exist elsewhere The project involves reaching a broach audience of

colleges and universities across the nation in an 8-month commitment to design build launch and fly a

payload(s) and vehicle components that support NASA research on high-power rockets to an altitude of

5280 feet above ground level (AGL) The challenge is based on team selection of multiple options There is

a Student Launch option that consists of 7 different experiments and a Centennial Challenge (CC) option

that consists of designing and building a Mars Ascent Vehicle (MAV) Supported by the Office of Education

Human Exploration and Operations (HEO) Mission Directorate Centennial Challenges Office and

commercial industry USLI is a unique NASA-specific opportunity to provide resources and experiences thatis built around a mission not textbook knowledge

After a competitive proposal selection process teams participate in a series of design reviews that are

submitted to NASA via a team-developed website These reviews mirror the NASA engineering design

lifecycle providing a NASA-unique experience that prepares individuals for the HEO workforce Teams must

successfully complete a Preliminary Design Review (PDR) Critical Design Review (CDR) Flight Readiness

Review (FRR) Launch Readiness Review (LRR) that includes safety briefings and an analysis of vehicle

systems ground support equipment and flight data Each team must pass a review in order to move to a

subsequent review Teams will present their PDR CDR and FRR to a review panel of scientists engineers

technicians and educators via video teleconference Review panel members the Range Safety Officer

(RSO) and Subject Matter Experts (SME) provide feedback and ask questions in order to increase the

fidelity between the USLI and research needs and will score each team according to a standard scoring

rubric The partnership of teams and NASA is win-win which not only benefits from the research conducted

by the teams but also prepares a potential future workforce familiar with the NASA Engineering Design

Lifecycle

College and university teams must successfully complete the requirements of Tasks 1 or 2 and are eligible

for awards through Student Launch Any team who wishes to incorporate additional research through the use

of a separate payload may do so The team must provide documentation in all reports and reviews oncomponents and systems outside of what is required for the project The Centennial Challenges Office will

award prizes to college university and non-academic teams for successful demonstration of the MAV (see

CC supplemental handbook) The USLI awards listed at the end of this handbook will only be given to teams

from an academic institution

4

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

NAS

A Pr

ojec

t Life

Cyc

le

Char

les P

ierc

eDe

puty

Chi

ef S

pace

craf

t amp A

uxili

ary

Prop

ulsio

n Sy

stem

s Bra

nch

NAS

A -M

arsh

all S

pace

Flig

ht C

ente

r

39

Topi

cs

bullPu

rpos

e O

bjec

tive

bullPr

ojec

t Life

Cyc

lebull

Syst

em R

equi

rem

ents

Rev

iew

(NA

to N

ASA

Stud

ent L

aunc

h)bull

Prel

imin

ary

Desig

nbull

Criti

cal (

Fina

l) De

sign

bullFl

ight

Rea

dine

ss

40

Purp

ose

Obj

ectiv

es

of th

e N

ASA

Proj

ect L

ife C

ycle

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an fo

r the

des

ign

bui

ld v

erifi

catio

n fl

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erat

ions

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osal

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esire

d sy

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etw

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and

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ndashPl

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eliv

erab

les

ndashFi

delit

yndash

Tim

ing

41

Typi

cal N

ASA

Proj

ect L

ife C

ycle

Refe

renc

e N

PR 71

205

D F

igur

e 2-

4 ldquo

The

NAS

A Pr

ojec

t Life

Cyc

lerdquo

42

Stud

ent L

aunc

h Pr

ojec

ts L

ife C

ycle

Phas

e A

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e B

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e C

Phas

e D

Phas

e E

Phas

e F

Acqu

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on amp

Pr

elim

inar

y De

sign

Fina

l Des

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Fabr

icat

ion

amp

Ope

ratio

ns amp

Di

spos

alRe

quire

men

tsLa

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Sust

ainm

ent

Auth

ority

to P

roce

edSR

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RCD

RFR

R Laun

chbull

ATP

(Aut

horit

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Proc

eed)

ndashFu

ndin

g is

appl

ied

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e co

ntra

cte

ffort

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wor

k per

form

ance

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n be

gin

bullSR

R (S

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m R

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iew

) ndashTo

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vel R

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d in

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stem

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ts S

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m R

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ewed

and

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iven

to p

roce

ed in

to

Prel

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ary

Desig

n T

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h Pr

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ep

bullPD

R (P

relim

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y Des

ign

Revi

ew) ndash

Prel

imin

ary

Desig

n is

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ewed

and

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horit

y is g

iven

to

proc

eed

into

Fin

al D

esig

nbull

CDR

(Crit

ical

Des

ign

Revi

ew) ndash

Fina

l Des

ign

is re

view

ed a

nd a

utho

rity i

s giv

en to

pro

ceed

to

build

the

syst

em

bullFR

R (F

light

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dine

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As-b

uilt

desig

n an

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ata

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ewed

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give

n fo

r Lau

nch

43

Prel

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ary

Desi

gn R

evie

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Obj

ectiv

endash

Prov

e th

e fe

asib

ility

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uild

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ch th

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at a

ll sy

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will

be

met

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Rece

ive

auth

ority

to p

roce

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the

Fina

l Des

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Phas

ebull

Typi

cal P

rodu

cts (

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cle

and

Payl

oad)

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hedu

le (d

esig

n b

uild

tes

t)ndash

Cost

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get S

tate

men

tndash

Prel

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n Pr

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of O

pera

tions

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Inte

rfac

es (w

ithin

the

syst

em an

d ex

tern

al to

the

syst

em)

ndashTe

st a

nd V

erifi

catio

n Pl

anndash

Gro

und

Supp

ort E

quip

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t Des

igns

Ide

ntifi

catio

nndash

Safe

ty F

eatu

res

44

Criti

cal D

esig

n Re

view

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bjec

tive

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mpl

ete

the

final

des

ign

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e ro

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ceiv

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Verif

icat

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e

bullTy

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l Pro

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hicl

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ured

to re

flect

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final

des

ign)

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port

and

dis

cuss

com

plet

ed te

sts

ndashPr

oced

ures

and

Che

cklis

ts

45

Flig

ht R

eadi

ness

Rev

iew

bullO

bjec

tive

ndashPr

ove

that

the

Rock

etP

aylo

ad Sy

stem

has

bee

n fu

lly b

uilt

test

ed a

nd v

erifi

ed

to m

eet t

he sy

stem

requ

irem

ents

ndashPr

ove

that

all

syst

em re

quire

men

ts h

ave

been

or w

ill b

e m

etndash

Rece

ive

auth

ority

to La

unch

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

Sche

dule

ndashCo

st S

tate

men

tndash

Desig

n O

verv

iew

bullKe

y com

pone

nts

bullKe

y dra

win

gs an

d la

yout

sbull

Traj

ecto

ry an

d ot

her k

ey a

naly

ses

bullM

ass S

tate

men

t bull

Rem

aini

ng R

isks

ndashM

issio

n Pr

ofile

ndash

Pres

enta

tion

and

anal

ysis

of te

st d

ata

ndashSy

stem

Req

uire

men

ts V

erifi

catio

nndash

Gro

und

Supp

ort E

quip

men

t ndash

Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Per

sonn

el

expo

sure

to

high

vol

tage

Con

tact

with

en

ergi

zed

lam

p ba

nk c

ircu

its

Dea

th o

r se

vere

pe

rson

nel i

njur

y 1C

1

D

urin

g te

st o

pera

tion

lam

p ba

nks

circ

uits

will

be

ener

gize

d on

ly w

hen

no

pers

onne

l are

insi

de c

ham

ber

2

D

oor

to c

ham

ber

wil

l be

clos

ed

prio

r to

ene

rgiz

ing

circ

uits

3

T

S30

0 ac

cess

con

trol

s ar

e in

pl

ace

for

the

test

1

304-

TC

P-0

16 S

ectio

n 3

13

requ

ires

di

sabl

ing

heat

er e

lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r 2

P

er 3

04-T

CP

-016

tes

ts w

ill o

nly

be

perf

orm

ed u

nder

per

sona

l dir

ectio

n of

Tes

t E

ngin

eer

3

Acc

ess

cont

rols

for

this

test

are

in

clud

ed in

304

-TC

P-0

16 T

hese

incl

ude

o

L

ower

Eas

t Tes

t Are

a G

ate

6 a

nd T

urn

C6

Lig

ht to

RE

D

o

Low

er E

ast T

est A

rea

Gat

e 7

and

Tur

n C

7 L

ight

to R

ED

o

L

ower

Eas

t Tes

t Are

a G

ate

8 a

nd T

urn

C8

Lig

ht to

RE

D

o

Ver

ify

all G

over

nmen

t spo

nsor

ed v

ehic

les

are

clea

r of

the

area

o

V

erif

y al

l non

-Gov

ernm

ent s

pons

ored

ve

hicl

es a

re c

lear

of

the

area

o

M

ake

the

follo

win

g an

noun

cem

ent

ldquoAtte

ntio

n al

l per

sonn

el t

est o

pera

tions

ar

e ab

out t

o be

gin

at T

S30

0 T

he a

rea

is

clea

red

for

the

Des

igna

ted

Cre

w O

nly

and

wil

l rem

ain

until

fur

ther

not

ice

rdquo (R

EP

EA

T)

1E

Per

sonn

el

expo

sure

to a

n ox

ygen

de

fici

ent

envi

ronm

ent

Ent

ry in

to 1

2 ft

ch

ambe

r w

ith

unkn

own

atm

osph

ere

Dea

th o

r se

vere

pe

rson

nel i

njur

y 1C

1

O

xyge

n m

onito

rs a

re s

tatio

ned

insi

de c

ham

ber

and

cham

ber

entr

yway

2

C

ham

ber

air

vent

ilat

or o

pera

ted

afte

r ea

ch p

anel

test

to v

ent c

ham

ber

1

304-

TC

P-0

16 r

equi

res

inst

alla

tion

of

the

Tes

t Art

icle

usi

ng ldquo

Tes

t Pan

el

Inst

allR

emov

al P

roce

dure

rdquo T

his

proc

edur

e re

quir

es u

se o

f a

port

able

O2

mon

itor

in th

e se

ctio

n en

title

d ldquoP

ost T

est A

ctiv

ities

and

Tes

t P

anel

Rem

oval

rdquo S

tep

1

2

304-

TC

P-0

16 S

ectio

n 3

122

req

uire

s C

ham

ber

Ven

t Sys

tem

to r

un f

or 3

+ M

inut

es

prio

r to

ent

erin

g th

e ch

ambe

r to

rem

ove

the

pane

l

1E

60

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

3

Atte

ndan

t will

be

post

ed o

utsi

de

cham

ber

to m

onit

or in

-cha

mbe

r ac

tivi

ties

fa

cili

tate

eva

cuat

ion

or r

escu

e if

req

uire

d

and

to r

estr

ict a

cces

s to

una

utho

rize

d pe

rson

nel

4

Fir

e D

ept

to b

e no

tifie

d th

at

conf

ined

spa

ce e

ntri

es a

re b

eing

mad

e

3

ldquoTes

t Pan

el I

nsta

llR

emov

al

Pro

cedu

rerdquo

pag

e 1

req

uire

s th

e us

e of

exi

stin

g M

ET

TS

con

fine

d sp

ace

entr

y pr

oced

ures

w

hich

incl

udes

req

uire

men

t for

an

atte

ndan

t w

hen

ente

ring

the

12 f

t vac

uum

cha

mbe

r re

fere

nce

Con

fine

d S

pace

Per

mit

0298

4

ldquoT

est P

anel

Ins

tall

Rem

oval

P

roce

dure

rdquo p

age

1 r

equi

res

the

use

of e

xist

ing

ME

TT

S c

onfi

ned

spac

e en

try

proc

edur

es

whi

ch in

clud

es r

equi

rem

ent t

o no

tify

the

Fir

e D

ept

prio

r to

ent

erin

g th

e 12

ft v

acuu

m

cham

ber

Ref

eren

ce C

onfi

ned

Spa

ce P

erm

it

0298

Per

sonn

el

expo

sure

to

lam

p th

erm

al

ener

gy

P

roxi

mit

y to

la

mps

whi

le

ener

gize

d

Acc

iden

tal

cont

act w

ith

lam

p or

ca

libra

tion

plat

e w

hile

out

Per

sonn

el b

urns

re

quir

ing

med

ical

tr

eatm

ent

3C

1

Dur

ing

test

ope

rati

on l

amp

bank

s ci

rcui

ts w

ill b

e en

ergi

zed

only

whe

n no

pe

rson

nel a

re in

side

cha

mbe

r

2

Doo

r to

cha

mbe

r w

ill c

lose

d pr

ior

to e

nerg

izin

g ci

rcui

ts

3

De s

igna

ted

pers

onne

l will

wea

r

leat

her

glov

es to

han

dle

calib

ratio

n pl

ate

if r

equi

red

1

304-

TC

P-0

16 S

ectio

n 3

13

requ

ires

di

sabl

ing

heat

er e

lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r

2

Per

304

-TC

P-0

16 t

ests

wil

l onl

y be

pe

rfor

med

und

er p

erso

nal d

irec

tion

of T

est

Eng

inee

r 3

30

4-T

CP

-16

Sec

tion

14

Haz

ards

and

C

ontr

ols

req

uire

s in

sula

ted

glov

es a

s re

quir

ed

if h

ot it

ems

need

to b

e ha

ndle

d

3E

61

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Fai

lure

of

pres

sure

sy

stem

s

Ove

r-pr

essu

riza

tion

Per

sonn

el in

jury

Equ

ipm

ent

dam

age

1C

1

TS

300

faci

lity

pres

sure

sys

tem

s ar

e ce

rtif

ied

2

P

er E

T10

test

eng

inee

r h

igh

puri

ty a

ir s

yste

m w

ill b

e us

ed a

t lt 1

50

psig

ope

rati

ng p

ress

ure

ther

efor

e ce

rtif

icat

ion

not r

equi

red

3

A

ll n

on-c

erti

fied

test

equ

ipm

ent i

s pn

eum

atic

ally

pre

ssur

e te

sted

to 1

50

of

Max

imum

All

owab

le W

orki

ng P

ress

ure

(MA

WP

)

1

Per

the

MS

FC

Pre

ssur

e S

yste

ms

Rep

ortin

g T

ool (

PS

RT

) f

acili

ty s

yste

ms

have

be

en r

ecer

tifie

d un

der

TL

WT

-CE

RT

-10-

TS

300-

RR

2002

unt

il 3

320

20 T

he

cert

ific

atio

n in

clud

es G

aseo

us H

eliu

m G

aseo

us

Hyd

roge

n G

aseo

us N

itro

gen

Hig

h Pu

rity

Air

L

iqui

d H

ydro

gen

and

Liq

uid

Nitr

ogen

sys

tem

s

2

304-

TC

P-0

16 S

tep

21

14 r

equi

res

HO

R-1

2-12

8 2

nd S

tage

HP

Air

HO

R t

o be

L

oade

d to

75p

sig

3

S

ee P

ress

ure

Tes

t Rep

ort P

TR

-001

455

(App

endi

x A

) A

ll no

n-ce

rtif

ied

equi

pmen

t has

a

min

imum

fac

tor

of s

afet

y of

41

1E

Foa

m p

anel

ca

tche

s fi

re

duri

ng te

stin

g

Tes

t req

uire

s hi

gh

heat

wit

h po

ssib

ility

of

pane

l bu

rnin

g

Rel

ease

of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

ion

requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

hed

Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

s so

ver

y lit

tle

or n

o re

sidu

al g

asse

s or

vap

ors

rem

ain

1

A m

inim

um v

enti

lati

on o

f th

e ch

ambe

r sh

ould

the

foam

pan

el b

urn

duri

ng o

r af

ter

test

ing

has

been

est

ablis

hed

by p

roce

dure

304

-T

CP

-016

whi

ch r

equi

res

the

min

imum

10

min

ute

vent

ilatio

n be

fore

per

sonn

el a

re a

llow

ed

to e

nter

Add

ition

ally

if

any

abno

rmal

ities

are

ob

serv

ed th

e In

dust

rial

Hea

lth r

epre

sent

ativ

e w

ill b

e ca

lled

to p

erfo

rm a

dditi

onal

air

sa

mpl

ing

befo

re p

erso

nnel

ent

ry

1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

1 Vehicle Requirements 11 The vehicle shall deliver the payload to an apogee altitude of 5280 feet above ground level (AGL)

12 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude

used in the competition scoring The altitude score will account for 10 of the teamrsquos overall competition

score Teams will receive the maximum number of altitude points (5280) if the official scoring altimeter

reads a value of exactly 5280 feet AGL The team will lose two points for every foot above the required

altitude and one point for every foot below the required altitude The altitude score will be equivalent to the percentage of altitude points remaining after any deductions

121The official scoring altimeter shall report the official competition altitude via a series of beeps to be checked after the competition flight

122Teams may have additional altimeters to control vehicle electronics and payload experiment(s) 1221 At the Launch Readiness Review a NASA official will mark the altimeter that will be used

for the official scoring

1222 At the launch field a NASA official will obtain the altitude by listening to the audible beeps reported by the official competition marked altimeter

1223 At the launch field to aid in determination of the vehiclersquos apogee all audible electronics except for the official altitude-determining altimeter shall be capable of being turned off

123The following circumstances will warrant a score of zero for the altitude portion of the competition

1231 The official marked altimeter is damaged andor does not report an altitude via a series of beeps after the teamrsquos competition flight

1232 The team does not report to the NASA official designated to record the altitude with their official marked altimeter on the day of the launch

1233 The altimeter reports an apogee altitude over 5600 feet AGL 1234 The rocket is not flown at the competition launch site

13 The launch vehicle shall be designed to be recoverable and reusable Reusable is defined as being able to launch again on the same day without repairs or modifications

14 The launch vehicle shall have a maximum of four (4) independent sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute

15 The launch vehicle shall be limited to a single stage

16 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens

17 The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component

18 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA-designated Range Services Provider

19 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR) Tripoli Rocketry Association (TRA) andor the Canadian Association of Rocketry (CAR)

191Final motor choices must be made by the Critical Design Review (CDR)

192Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO) and will only be approved if the change is for the sole purpose of increasing the safety margin

110The total impulse provided by a launch vehicle shall not exceed 5120 Newton-seconds (L-class) 111 Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria

1111 The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 41 with supporting design documentation included in all milestone reviews

1112 Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank

5

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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A Pr

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43

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44

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45

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erifi

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edur

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s

46

Haza

rd A

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Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

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r pro

ject

or t

he

envi

ronm

ent

A cl

assic

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e of

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azar

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a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

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rts

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of w

hich

pla

y in

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how

we

cate

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e it

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we

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ond

ndashN

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ll ha

zard

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life

thre

aten

ing

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ave

cata

stro

phic

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es T

hey

can

be m

ore

beni

gn

like

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and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

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iptio

n

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zard

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crip

tion

is co

mpo

sed

of 3

par

ts

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zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

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ly w

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D

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T

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sabl

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304

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Haz

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304

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Haz

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glov

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61

Haz

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faci

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A

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Max

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unt

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320

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304-

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41

1E

Foa

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stin

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Tes

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Byp

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ve

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eva

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Hyg

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min

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noug

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304

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whi

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min

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10

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re a

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Add

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if

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mpl

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1E

62

Und

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MS

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By

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MS

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nviro

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tal H

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63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

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oduc

ed b

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man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

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in

tend

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giv

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com

preh

ensi

ve o

verv

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of h

ow

to s

afel

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ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

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SD

S

M

SD

Srsquos

do

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a st

anda

rd fo

rmat

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hav

e ce

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in

form

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n pe

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HA

29

CFR

191

012

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Man

ufac

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men

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f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

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and

com

mon

nam

es

Phy

sica

l and

che

mic

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hara

cter

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s

Phy

sica

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H

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haz

ards

R

oute

s of

ent

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Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

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nici

ty

Pro

cedu

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for s

afe

hand

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and

use

C

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Em

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Firs

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D

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of la

st M

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S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

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ieni

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evel

op a

nd p

ublis

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cupa

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osur

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r man

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emic

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its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

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amon

g ot

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thin

gs e

stab

lishe

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stem

use

d on

man

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bels

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azar

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ch

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atio

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ility

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caut

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An

exa

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NFP

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xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

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iona

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titut

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upat

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agen

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lic H

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and

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irato

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nd

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sam

plin

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s I

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o in

vest

igat

es

inci

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s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

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and

Hea

lth

Adm

inis

tratio

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a F

eder

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genc

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issi

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mak

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re th

at th

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fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

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osur

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its a

re d

esig

ned

to re

flect

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xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

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ash

poin

t

The

lowe

st te

mpe

ratu

re a

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ch th

e ch

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al c

an fo

rm a

n ig

nita

ble

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ture

with

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U

pper

(UE

L) a

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wer

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losi

ve li

mits

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inue

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osio

n a

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the

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spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

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xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

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n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

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mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

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AN

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OM

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FICA

TIO

N

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L IN

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N S

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MS

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C14

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LIN

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REET

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GS

(SCA

LE 0

-4)

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lth=

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=0

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GEN

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ORM

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ICAL

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ARD

S F

lam

mab

le li

quid

and

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apor

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se fl

ash

fire

Goo

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ners

23

0

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NTI

AL H

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TS

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IRST

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5 F

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FIG

HTI

NG

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Wha

t sho

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you

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s it

caus

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85

SECT

ION

6 A

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ENTA

L R

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Redu

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7 H

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SECT

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8 E

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RO

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MET

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(59

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86

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9 P

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(80

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R PR

ESSU

RE 1

00 m

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IFIC

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VITY

(w

ater

= 1

) 0

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ATER

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LITY

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R TH

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TIO

N R

ATE

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(et

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OSI

TY 0

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SOLV

ENT

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BILI

TY a

lcoh

ol e

ther

ben

zene

ace

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oils

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vent

s

MYT

H i

f it

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ls b

ad it

is h

arm

ful

if it

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ls g

ood

it is

saf

e

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or is

hea

vier

than

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id w

ill fl

oat o

n st

agna

nt w

ater

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ver

y so

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e in

wat

er

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like

ly s

mel

l MEK

bef

ore

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g ov

erex

pose

d

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s to

vap

or e

asy

87

SECT

ION

10

STA

BILI

TY A

ND

REA

CTIV

ITY

SECT

ION

11

TO

XICO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

12

ECO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

13

DIS

POSA

L CO

NSI

DER

ATIO

NS

SECT

ION

14

TR

ANSP

ORT

INFO

RM

ATIO

N

SECT

ION

15

REG

ULA

TOR

Y IN

FOR

MAT

ION

SECT

ION

16

OTH

ER IN

FOR

MAT

ION

MSD

Srsquos

have

an

abun

danc

e of

in

form

atio

n us

eful

in

man

y di

ffer

ent

aspe

cts

88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

1113 Full pedigree of the tank shall be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when

112 All teams shall successfully launch and recover a subscale model of their full-scale rocket prior to CDR

The subscale model should resemble and perform as similarly as possible to the full-scale model

however the full-scale shall not be used as the subscale model

113 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of

the full-scale demonstration flight is to demonstrate the launch vehiclersquos stability structural integrity

recovery systems and the teamrsquos ability to prepare the launch vehicle for flight A successful flight is

defined as a launch in which all hardware is functioning properly (ie drogue chute at apogee main

chute at a lower altitude functioning tracking devices etc) The following criteria must be met during the

full scale demonstration flight

1131 The vehicle and recovery system shall have functioned as designed 1132 The payload does not have to be flown during the full-scale test flight The following

requirements still apply

11321 If the payload is not flown mass simulators shall be used to simulate the payload mass

11322 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass

11323 If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle those systems shall be active during the full-scale demonstration flight

1133 The full-scale motor does not have to be flown during the full-scale test flight However it is

recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification If the full-scale motor is not flown during the full-scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight

1134 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight Fully

ballasted refers to the same amount of ballast that will be flown during the competition flight

1135 After successfully completing the full-scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer (RSO)

114Each team will have a maximum budget of $7500 they may spend on the rocket and its payload(s) (Exception Centennial Challenge payload task See supplemental requirements at httpwwwnasagovmavprize for more information) The cost is for the competition rocket and payload as it sits on the pad including all purchased components The fair market value of all donated items or

materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle

Shipping costs

Team labor costs

6

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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edur

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s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

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exa

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e of

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azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

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of w

hich

pla

y in

to

how

we

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e it

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ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

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ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

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re-

RA

C

Mit

igat

ion

Ver

ific

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T

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Tes

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304

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Add

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1E

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Und

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By

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MS

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nviro

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63

Wha

t is

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SD

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A

Mat

eria

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Dat

a S

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(M

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man

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tend

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preh

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with

or h

andl

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is

chem

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64

Wha

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M

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Srsquos

do

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y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

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ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

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MET

HYL

ACE

TON

E 3

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TAN

ON

E M

EK

SCO

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P reg

BRA

ND

SO

LVEN

T

3 (3

M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

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RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

ress

ion

PHYS

ICAL

HAZ

ARD

S F

lam

mab

le li

quid

and

vap

or V

apor

may

cau

se fl

ash

fire

Goo

d in

fo fo

rla

belin

g co

ntai

ners

23

0

POTE

NTI

AL H

EALT

H E

FFEC

TS

INH

ALAT

ION

SH

ORT

TER

M E

XPO

SURE

irr

itatio

n n

ause

a v

omiti

ng d

iffic

ulty

bre

athi

ng

Wha

t hap

pens

whe

n ex

pose

d

84

SKIN

CO

NTA

CT

SHO

RT T

ERM

EXP

OSU

RE i

rrita

tion

LON

G T

ERM

EXP

OSU

RE s

ame

as e

ffect

s re

port

ed in

sho

rt t

erm

exp

osur

eEY

E CO

NTA

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ESTI

ON

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INO

GEN

STA

TUS

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A N

NTP

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RC N

SECT

ION

4 F

IRST

AID

MEA

SUR

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HAL

ATIO

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SKIN

CO

NTA

CThellip

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TACT

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GES

TIO

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SECT

ION

5 F

IRE

FIG

HTI

NG

MEA

SUR

ES

Wha

t sho

uld

you

do if

exp

osed

Doe

s it

caus

e ca

ncer

85

SECT

ION

6 A

CCID

ENTA

L R

ELEA

SE M

EASU

RES

AIR

RELE

ASE

Redu

ce v

apor

s w

ith w

ater

spr

aySO

IL R

ELEA

SE

Dig

hol

ding

are

a su

ch a

s la

goon

pon

d or

pit

for

cont

ainm

ent

Abs

orb

with

hellip

SECT

ION

7 H

AND

LIN

G A

ND

STO

RAG

E

Stor

e an

d ha

ndle

in a

ccor

danc

e hellip

SECT

ION

8 E

XPO

SUR

E CO

NTR

OLS

PER

SON

AL P

RO

TECT

ION

EXPO

SURE

LIM

ITS

MET

HYL

ETH

YL K

ETO

NE

MET

HYL

ETH

YL K

ETO

NE

200

ppm

(59

0 m

gm

3) O

SHA

TWA

300

ppm

(88

5 m

gm

3) O

SHA

STEL

200

ppm

(59

0 m

gm

3) A

CGIH

TW

A30

0 pp

m (

885

mg

m3)

ACG

IH S

TEL

8 hr

avg

15 m

in a

vg

86

SECT

ION

9 P

HYS

ICAL

AN

D C

HEM

ICAL

PR

OPE

RTIE

S

COLO

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olor

less

PHYS

ICAL

FO

RM l

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inty

sw

eet o

dor

MO

LECU

LAR

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T 7

212

MO

LECU

LAR

FORM

ULA

C-H

3-C-

H2-

C-O

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ILIN

G P

OIN

T 1

76 F

(80

C)

FREE

ZIN

G P

OIN

T -1

23 F

(-8

6 C)

VAPO

R PR

ESSU

RE 1

00 m

mH

g

25

CVA

POR

DEN

SITY

(ai

r =

1)

25

SPEC

IFIC

GRA

VITY

(w

ater

= 1

) 0

805

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ATER

SO

LUBI

LITY

27

5PH

No

data

ava

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eVO

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LITY

No

data

ava

ilabl

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DO

R TH

RESH

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02

5-10

ppm

EVAP

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TIO

N R

ATE

27

(et

her =

1)

VISC

OSI

TY 0

40

cP

25 C

SOLV

ENT

SOLU

BILI

TY a

lcoh

ol e

ther

ben

zene

ace

tone

oils

sol

vent

s

MYT

H i

f it

smel

ls b

ad it

is h

arm

ful

if it

smel

ls g

ood

it is

saf

e

MEK

vap

or is

hea

vier

than

air

MEK

liqu

id w

ill fl

oat o

n st

agna

nt w

ater

Not

ver

y so

lubl

e in

wat

er

Will

like

ly s

mel

l MEK

bef

ore

bein

g ov

erex

pose

d

Goe

s to

vap

or e

asy

87

SECT

ION

10

STA

BILI

TY A

ND

REA

CTIV

ITY

SECT

ION

11

TO

XICO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

12

ECO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

13

DIS

POSA

L CO

NSI

DER

ATIO

NS

SECT

ION

14

TR

ANSP

ORT

INFO

RM

ATIO

N

SECT

ION

15

REG

ULA

TOR

Y IN

FOR

MAT

ION

SECT

ION

16

OTH

ER IN

FOR

MAT

ION

MSD

Srsquos

have

an

abun

danc

e of

in

form

atio

n us

eful

in

man

y di

ffer

ent

aspe

cts

88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

115Vehicle Prohibitions 1151The launch vehicle shall not utilize forward canards 1152The launch vehicle shall not utilize forward firing motors

1153The launch vehicle shall not utilize motors that expel titanium sponges (Sparky Skidmark MetalStorm etc)

1154The launch vehicle shall not utilize hybrid motors

1155The launch vehicle shall not utilize a cluster of motors

2 Recovery System Requirements 21 The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible provided the kinetic energy during drogue-stage descent is reasonable as deemed by the Range Safety Officer

22 Teams must perform a successful ground ejection test for both the drogue and main parachutes This must

be done prior to the initial subscale and full scale launches

23 At landing each independent section of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf

24 The recovery system electrical circuits shall be completely independent of any payload electrical circuits

25 The recovery system shall contain redundant commercially available altimeters The term ldquoaltimetersrdquo includes both simple altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter

26 Motor ejection is not a permissible form of primary or secondary deployment An electronic form of deployment must be used for deployment purposes

27 A dedicated arming switch shall arm each altimeter which is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad

28 Each altimeter shall have a dedicated power supply

29 Each arming switch shall be capable of being locked in the ON position for launch

210 Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment

211An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver

2111 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device

2112 The electronic tracking device shall be fully functional during the official flight at the competition launch site

7

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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46

Haza

rd A

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Intr

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anag

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47

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t is a

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Put s

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ad

vers

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fect

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ject

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ronm

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re o

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losio

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ore

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r sch

edul

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tbac

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48

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rd D

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n

A ha

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of 3

par

ts

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zard

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imes

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Haza

rdou

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itiat

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even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

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lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

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Per

sonn

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Con

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p ba

nk c

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circ

uits

will

be

ener

gize

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ly w

hen

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pers

onne

l are

insi

de c

ham

ber

2

D

oor

to c

ham

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wil

l be

clos

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prio

r to

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rgiz

ing

circ

uits

3

T

S30

0 ac

cess

con

trol

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pl

ace

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the

test

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304-

TC

P-0

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sabl

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304

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tion

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Dur

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304

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req

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ted

glov

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s re

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if h

ot it

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need

to b

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61

Haz

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Equ

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faci

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Max

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unt

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320

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304-

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41

1E

Foa

m p

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s fi

re

duri

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stin

g

Tes

t req

uire

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gh

heat

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of

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rnin

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Rel

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of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

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requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

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Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

s so

ver

y lit

tle

or n

o re

sidu

al g

asse

s or

vap

ors

rem

ain

1

A m

inim

um v

enti

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on o

f th

e ch

ambe

r sh

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the

foam

pan

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urn

duri

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r af

ter

test

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has

been

est

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hed

by p

roce

dure

304

-T

CP

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whi

ch r

equi

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the

min

imum

10

min

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vent

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n be

fore

per

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el a

re a

llow

ed

to e

nter

Add

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ally

if

any

abno

rmal

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are

ob

serv

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e In

dust

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Hea

lth r

epre

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ativ

e w

ill b

e ca

lled

to p

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dditi

onal

air

sa

mpl

ing

befo

re p

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nnel

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ry

1E

62

Und

erst

andi

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MS

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rsquos

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MS

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nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

-3RT

ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

NE

MET

HYL

ACE

TON

E 3

-BU

TAN

ON

E M

EK

SCO

TCH

-GRI

P reg

BRA

ND

SO

LVEN

T

3 (3

M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

-3PE

RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

ress

ion

PHYS

ICAL

HAZ

ARD

S F

lam

mab

le li

quid

and

vap

or V

apor

may

cau

se fl

ash

fire

Goo

d in

fo fo

rla

belin

g co

ntai

ners

23

0

POTE

NTI

AL H

EALT

H E

FFEC

TS

INH

ALAT

ION

SH

ORT

TER

M E

XPO

SURE

irr

itatio

n n

ause

a v

omiti

ng d

iffic

ulty

bre

athi

ng

Wha

t hap

pens

whe

n ex

pose

d

84

SKIN

CO

NTA

CT

SHO

RT T

ERM

EXP

OSU

RE i

rrita

tion

LON

G T

ERM

EXP

OSU

RE s

ame

as e

ffect

s re

port

ed in

sho

rt t

erm

exp

osur

eEY

E CO

NTA

CThellip

ING

ESTI

ON

hellip

CARC

INO

GEN

STA

TUS

OSH

A N

NTP

NIA

RC N

SECT

ION

4 F

IRST

AID

MEA

SUR

ESIN

HAL

ATIO

Nhellip

SKIN

CO

NTA

CThellip

EYE

CON

TACT

hellipIN

GES

TIO

Nhellip

SECT

ION

5 F

IRE

FIG

HTI

NG

MEA

SUR

ES

Wha

t sho

uld

you

do if

exp

osed

Doe

s it

caus

e ca

ncer

85

SECT

ION

6 A

CCID

ENTA

L R

ELEA

SE M

EASU

RES

AIR

RELE

ASE

Redu

ce v

apor

s w

ith w

ater

spr

aySO

IL R

ELEA

SE

Dig

hol

ding

are

a su

ch a

s la

goon

pon

d or

pit

for

cont

ainm

ent

Abs

orb

with

hellip

SECT

ION

7 H

AND

LIN

G A

ND

STO

RAG

E

Stor

e an

d ha

ndle

in a

ccor

danc

e hellip

SECT

ION

8 E

XPO

SUR

E CO

NTR

OLS

PER

SON

AL P

RO

TECT

ION

EXPO

SURE

LIM

ITS

MET

HYL

ETH

YL K

ETO

NE

MET

HYL

ETH

YL K

ETO

NE

200

ppm

(59

0 m

gm

3) O

SHA

TWA

300

ppm

(88

5 m

gm

3) O

SHA

STEL

200

ppm

(59

0 m

gm

3) A

CGIH

TW

A30

0 pp

m (

885

mg

m3)

ACG

IH S

TEL

8 hr

avg

15 m

in a

vg

86

SECT

ION

9 P

HYS

ICAL

AN

D C

HEM

ICAL

PR

OPE

RTIE

S

COLO

R c

olor

less

PHYS

ICAL

FO

RM l

iqui

dO

DO

R m

inty

sw

eet o

dor

MO

LECU

LAR

WEI

GH

T 7

212

MO

LECU

LAR

FORM

ULA

C-H

3-C-

H2-

C-O

-C-H

3BO

ILIN

G P

OIN

T 1

76 F

(80

C)

FREE

ZIN

G P

OIN

T -1

23 F

(-8

6 C)

VAPO

R PR

ESSU

RE 1

00 m

mH

g

25

CVA

POR

DEN

SITY

(ai

r =

1)

25

SPEC

IFIC

GRA

VITY

(w

ater

= 1

) 0

805

4W

ATER

SO

LUBI

LITY

27

5PH

No

data

ava

ilabl

eVO

LATI

LITY

No

data

ava

ilabl

eO

DO

R TH

RESH

OLD

02

5-10

ppm

EVAP

ORA

TIO

N R

ATE

27

(et

her =

1)

VISC

OSI

TY 0

40

cP

25 C

SOLV

ENT

SOLU

BILI

TY a

lcoh

ol e

ther

ben

zene

ace

tone

oils

sol

vent

s

MYT

H i

f it

smel

ls b

ad it

is h

arm

ful

if it

smel

ls g

ood

it is

saf

e

MEK

vap

or is

hea

vier

than

air

MEK

liqu

id w

ill fl

oat o

n st

agna

nt w

ater

Not

ver

y so

lubl

e in

wat

er

Will

like

ly s

mel

l MEK

bef

ore

bein

g ov

erex

pose

d

Goe

s to

vap

or e

asy

87

SECT

ION

10

STA

BILI

TY A

ND

REA

CTIV

ITY

SECT

ION

11

TO

XICO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

12

ECO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

13

DIS

POSA

L CO

NSI

DER

ATIO

NS

SECT

ION

14

TR

ANSP

ORT

INFO

RM

ATIO

N

SECT

ION

15

REG

ULA

TOR

Y IN

FOR

MAT

ION

SECT

ION

16

OTH

ER IN

FOR

MAT

ION

MSD

Srsquos

have

an

abun

danc

e of

in

form

atio

n us

eful

in

man

y di

ffer

ent

aspe

cts

88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

Task 1 (select any 2) Task 2 311 Atmospheric Measurements 318 Centennial Challenge ndash MAV 312 Landing Hazards Detection 313 Liquid Sloshing in Micro-G 314 Propulsion System Analysis 315 Payload Fairing Design and

Deployment 316 Aerodynamic Analysis 317 Design your own (limit of

one)

212The recovery system electronics shall not be adversely affected by any other on-board electronic devices during flight (from launch until landing)

2121 The recovery system altimeters shall be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device andor magnetic wave producing

device

2122 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics

2123 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves (such as generators solenoid valves and Tesla coils) to avoid inadvertent excitation of the recovery system

2124 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics

3 Competition and Payload Requirements Each team shall choose any 2 payloads from Task 1 or have the choice to participate in the Centennial Challenge competition (Task 2)

31 The payload shall be designed to be recoverable and reusable Reusable is defined as being able to be launched again on the same day without repairs or modifications

32 (Task1) The team may choose to participate in 2 of the following payload options 321A payload that shall gather data for studying the atmosphere during descent and after landing

including measurements of pressure temperature relative humidity solar irradiance and ultraviolet radiation

3211 Measurements shall be made at least once every second during descent and every 60 seconds after landing Data collection shall terminate 10 minutes after landing

3212 The payload shall take at least 2 pictures during descent and 3 after landing The payload shall remain in orientation during descent and after landing such that the pictures taken portray the sky towards the top of the frame and the ground towards the bottom of the frame

3213 The data from the payload shall be stored onboard and transmitted wirelessly to the teamrsquos ground station at the time of completion of all surface operations

322A payload that scans the surface continuously during descent in order to detect potential landing hazards

3221 The data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present

3222 The data collected shall be stored on board and transmitted wirelessly to the teamrsquos ground station

323Liquid sloshing research in microgravity to support liquid propulsion systems

8

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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46

Haza

rd A

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Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

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outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

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r pro

ject

or t

he

envi

ronm

ent

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e of

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azar

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re o

r Exp

losio

nndash

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zard

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rts

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of w

hich

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y in

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e it

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ll ha

zard

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thre

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ave

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stro

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es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

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ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

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lts in

serio

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jury

to

pers

onne

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Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

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re-

RA

C

Mit

igat

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Ver

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T

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41

1E

Foa

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Tes

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304

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Add

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if

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serv

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mpl

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1E

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Und

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MS

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MS

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nviro

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63

Wha

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Mat

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Dat

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man

ufac

ture

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tend

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preh

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verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

-3RT

ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

NE

MET

HYL

ACE

TON

E 3

-BU

TAN

ON

E M

EK

SCO

TCH

-GRI

P reg

BRA

ND

SO

LVEN

T

3 (3

M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

-3PE

RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

ress

ion

PHYS

ICAL

HAZ

ARD

S F

lam

mab

le li

quid

and

vap

or V

apor

may

cau

se fl

ash

fire

Goo

d in

fo fo

rla

belin

g co

ntai

ners

23

0

POTE

NTI

AL H

EALT

H E

FFEC

TS

INH

ALAT

ION

SH

ORT

TER

M E

XPO

SURE

irr

itatio

n n

ause

a v

omiti

ng d

iffic

ulty

bre

athi

ng

Wha

t hap

pens

whe

n ex

pose

d

84

SKIN

CO

NTA

CT

SHO

RT T

ERM

EXP

OSU

RE i

rrita

tion

LON

G T

ERM

EXP

OSU

RE s

ame

as e

ffect

s re

port

ed in

sho

rt t

erm

exp

osur

eEY

E CO

NTA

CThellip

ING

ESTI

ON

hellip

CARC

INO

GEN

STA

TUS

OSH

A N

NTP

NIA

RC N

SECT

ION

4 F

IRST

AID

MEA

SUR

ESIN

HAL

ATIO

Nhellip

SKIN

CO

NTA

CThellip

EYE

CON

TACT

hellipIN

GES

TIO

Nhellip

SECT

ION

5 F

IRE

FIG

HTI

NG

MEA

SUR

ES

Wha

t sho

uld

you

do if

exp

osed

Doe

s it

caus

e ca

ncer

85

SECT

ION

6 A

CCID

ENTA

L R

ELEA

SE M

EASU

RES

AIR

RELE

ASE

Redu

ce v

apor

s w

ith w

ater

spr

aySO

IL R

ELEA

SE

Dig

hol

ding

are

a su

ch a

s la

goon

pon

d or

pit

for

cont

ainm

ent

Abs

orb

with

hellip

SECT

ION

7 H

AND

LIN

G A

ND

STO

RAG

E

Stor

e an

d ha

ndle

in a

ccor

danc

e hellip

SECT

ION

8 E

XPO

SUR

E CO

NTR

OLS

PER

SON

AL P

RO

TECT

ION

EXPO

SURE

LIM

ITS

MET

HYL

ETH

YL K

ETO

NE

MET

HYL

ETH

YL K

ETO

NE

200

ppm

(59

0 m

gm

3) O

SHA

TWA

300

ppm

(88

5 m

gm

3) O

SHA

STEL

200

ppm

(59

0 m

gm

3) A

CGIH

TW

A30

0 pp

m (

885

mg

m3)

ACG

IH S

TEL

8 hr

avg

15 m

in a

vg

86

SECT

ION

9 P

HYS

ICAL

AN

D C

HEM

ICAL

PR

OPE

RTIE

S

COLO

R c

olor

less

PHYS

ICAL

FO

RM l

iqui

dO

DO

R m

inty

sw

eet o

dor

MO

LECU

LAR

WEI

GH

T 7

212

MO

LECU

LAR

FORM

ULA

C-H

3-C-

H2-

C-O

-C-H

3BO

ILIN

G P

OIN

T 1

76 F

(80

C)

FREE

ZIN

G P

OIN

T -1

23 F

(-8

6 C)

VAPO

R PR

ESSU

RE 1

00 m

mH

g

25

CVA

POR

DEN

SITY

(ai

r =

1)

25

SPEC

IFIC

GRA

VITY

(w

ater

= 1

) 0

805

4W

ATER

SO

LUBI

LITY

27

5PH

No

data

ava

ilabl

eVO

LATI

LITY

No

data

ava

ilabl

eO

DO

R TH

RESH

OLD

02

5-10

ppm

EVAP

ORA

TIO

N R

ATE

27

(et

her =

1)

VISC

OSI

TY 0

40

cP

25 C

SOLV

ENT

SOLU

BILI

TY a

lcoh

ol e

ther

ben

zene

ace

tone

oils

sol

vent

s

MYT

H i

f it

smel

ls b

ad it

is h

arm

ful

if it

smel

ls g

ood

it is

saf

e

MEK

vap

or is

hea

vier

than

air

MEK

liqu

id w

ill fl

oat o

n st

agna

nt w

ater

Not

ver

y so

lubl

e in

wat

er

Will

like

ly s

mel

l MEK

bef

ore

bein

g ov

erex

pose

d

Goe

s to

vap

or e

asy

87

SECT

ION

10

STA

BILI

TY A

ND

REA

CTIV

ITY

SECT

ION

11

TO

XICO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

12

ECO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

13

DIS

POSA

L CO

NSI

DER

ATIO

NS

SECT

ION

14

TR

ANSP

ORT

INFO

RM

ATIO

N

SECT

ION

15

REG

ULA

TOR

Y IN

FOR

MAT

ION

SECT

ION

16

OTH

ER IN

FOR

MAT

ION

MSD

Srsquos

have

an

abun

danc

e of

in

form

atio

n us

eful

in

man

y di

ffer

ent

aspe

cts

88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

324Structural and dynamic analysis of airframe propulsion and electrical systems during boost 3241 The team must use and array of electrical sensors to measure structural vibration

and to measure the stress and strain of the rocket in the axial and radial directions 3242 At a minimum structural analysis shall be performed on the finsfin joints all

separation points and the nose cone 325A payload fairing design and deployment mechanism

3251 The fairings and payload must be tethered to the main body to prevent small objects from getting lost in the field

326An aerodynamic analysis of structural protuberances 327Design your own payload (limit of 1) Must be approved by NASA review team

33 (Task 2) Centennial Challenge

NASA University Student Launch Initiative is collaborating with the NASA Centennial Challenges Mars Ascent Vehicle (MAV) Project to offer teams the chance to design and build autonomous ground support equipment (AGSE) The Centennial Challenges Program part of NASArsquos Science and Technology Mission Directorate awards incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation The goal of the MAV and its AGSE is to capture a simulated Martian payload sample seal it within a launch vehicle and prepare the vehicle for launch without the input from a human operator For specific rules regarding the MAV project and to learn more about Centennial Challenges please visit the Centennial Challenge website at httpwwwnasagovmavprize and review their project handbook NOTE The Centennial Challenge handbook is meant to be a complement to this handbook If a team chooses to participate in the Centennial Challenge they must abide by all the rules presented in this document

4 Safety Requirements

41 Each team shall use a launch and safety checklist The final checklists shall be included in the FRR report and used during the Launch Readiness Review (LRR) and launch day operations

42 For all academic institution teams a student safety officer shall be identified and shall be responsible for all items in section 43 For competing non-academic teams one participant who is not serving in the team mentor role shall serve as the designated safety officer

43 The role and responsibilities of each safety officer shall include but not limited to 431Monitor team activities with an emphasis on Safety during

4311 Design of vehicle and launcher 4312 Construction of vehicle and launcher 4313 Assembly of vehicle and launcher 4314 Ground testing of vehicle and launcher 4315 Sub-scale launch test(s) 4316 Full-scale launch test(s) 4317 Competition launch 4318 Recovery activities 4319 Educational Engagement activities

432Implement procedures developed by the team for construction assembly launch and recovery activities

433Manage and maintain current revisions of the teamrsquos hazard analyses failure modes analyses procedures and MSDSchemical inventory data

434Assist in the writing and development of the teamrsquos hazard analyses failure modes analyses and procedures

9

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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46

Haza

rd A

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oduc

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anag

ing

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47

Wha

t is a

Haz

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Put s

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ad

vers

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fect

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ject

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ronm

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re o

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losio

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rts

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e it

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zard

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ave

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hey

can

be m

ore

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gn

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ing

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r sch

edul

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ks

48

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rd D

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iptio

n

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mpo

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of 3

par

ts

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zard

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imes

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led

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Haza

rdou

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itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

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illin

g Hy

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hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

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zard

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rant

sRi

sk is

def

ined

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2 fa

ctor

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Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

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D

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T

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TC

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sabl

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61

Haz

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faci

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A

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Max

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320

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41

1E

Foa

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Tes

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Byp

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irem

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min

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304

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10

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Add

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if

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mpl

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1E

62

Und

erst

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MS

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By

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MS

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nviro

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63

Wha

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SD

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A

Mat

eria

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Dat

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(M

SD

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man

ufac

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parti

cula

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tend

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preh

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ork

with

or h

andl

e th

is

chem

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64

Wha

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Srsquos

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e ce

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form

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29

CFR

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Man

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ard

in

diffe

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65

Req

uire

d da

ta fo

r MS

DS

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Id

entit

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haz

ardo

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hem

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C

hem

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and

com

mon

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Phy

sica

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Phy

sica

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H

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R

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Exp

osur

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its

66

Req

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r MSD

Srsquos

(Con

t)

C

arci

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Pro

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for s

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use

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Em

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Firs

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pdat

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Man

ufac

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add

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pho

ne

num

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67

Impo

rtant

Age

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Amer

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Con

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ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

-3RT

ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

NE

MET

HYL

ACE

TON

E 3

-BU

TAN

ON

E M

EK

SCO

TCH

-GRI

P reg

BRA

ND

SO

LVEN

T

3 (3

M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

-3PE

RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

ress

ion

PHYS

ICAL

HAZ

ARD

S F

lam

mab

le li

quid

and

vap

or V

apor

may

cau

se fl

ash

fire

Goo

d in

fo fo

rla

belin

g co

ntai

ners

23

0

POTE

NTI

AL H

EALT

H E

FFEC

TS

INH

ALAT

ION

SH

ORT

TER

M E

XPO

SURE

irr

itatio

n n

ause

a v

omiti

ng d

iffic

ulty

bre

athi

ng

Wha

t hap

pens

whe

n ex

pose

d

84

SKIN

CO

NTA

CT

SHO

RT T

ERM

EXP

OSU

RE i

rrita

tion

LON

G T

ERM

EXP

OSU

RE s

ame

as e

ffect

s re

port

ed in

sho

rt t

erm

exp

osur

eEY

E CO

NTA

CThellip

ING

ESTI

ON

hellip

CARC

INO

GEN

STA

TUS

OSH

A N

NTP

NIA

RC N

SECT

ION

4 F

IRST

AID

MEA

SUR

ESIN

HAL

ATIO

Nhellip

SKIN

CO

NTA

CThellip

EYE

CON

TACT

hellipIN

GES

TIO

Nhellip

SECT

ION

5 F

IRE

FIG

HTI

NG

MEA

SUR

ES

Wha

t sho

uld

you

do if

exp

osed

Doe

s it

caus

e ca

ncer

85

SECT

ION

6 A

CCID

ENTA

L R

ELEA

SE M

EASU

RES

AIR

RELE

ASE

Redu

ce v

apor

s w

ith w

ater

spr

aySO

IL R

ELEA

SE

Dig

hol

ding

are

a su

ch a

s la

goon

pon

d or

pit

for

cont

ainm

ent

Abs

orb

with

hellip

SECT

ION

7 H

AND

LIN

G A

ND

STO

RAG

E

Stor

e an

d ha

ndle

in a

ccor

danc

e hellip

SECT

ION

8 E

XPO

SUR

E CO

NTR

OLS

PER

SON

AL P

RO

TECT

ION

EXPO

SURE

LIM

ITS

MET

HYL

ETH

YL K

ETO

NE

MET

HYL

ETH

YL K

ETO

NE

200

ppm

(59

0 m

gm

3) O

SHA

TWA

300

ppm

(88

5 m

gm

3) O

SHA

STEL

200

ppm

(59

0 m

gm

3) A

CGIH

TW

A30

0 pp

m (

885

mg

m3)

ACG

IH S

TEL

8 hr

avg

15 m

in a

vg

86

SECT

ION

9 P

HYS

ICAL

AN

D C

HEM

ICAL

PR

OPE

RTIE

S

COLO

R c

olor

less

PHYS

ICAL

FO

RM l

iqui

dO

DO

R m

inty

sw

eet o

dor

MO

LECU

LAR

WEI

GH

T 7

212

MO

LECU

LAR

FORM

ULA

C-H

3-C-

H2-

C-O

-C-H

3BO

ILIN

G P

OIN

T 1

76 F

(80

C)

FREE

ZIN

G P

OIN

T -1

23 F

(-8

6 C)

VAPO

R PR

ESSU

RE 1

00 m

mH

g

25

CVA

POR

DEN

SITY

(ai

r =

1)

25

SPEC

IFIC

GRA

VITY

(w

ater

= 1

) 0

805

4W

ATER

SO

LUBI

LITY

27

5PH

No

data

ava

ilabl

eVO

LATI

LITY

No

data

ava

ilabl

eO

DO

R TH

RESH

OLD

02

5-10

ppm

EVAP

ORA

TIO

N R

ATE

27

(et

her =

1)

VISC

OSI

TY 0

40

cP

25 C

SOLV

ENT

SOLU

BILI

TY a

lcoh

ol e

ther

ben

zene

ace

tone

oils

sol

vent

s

MYT

H i

f it

smel

ls b

ad it

is h

arm

ful

if it

smel

ls g

ood

it is

saf

e

MEK

vap

or is

hea

vier

than

air

MEK

liqu

id w

ill fl

oat o

n st

agna

nt w

ater

Not

ver

y so

lubl

e in

wat

er

Will

like

ly s

mel

l MEK

bef

ore

bein

g ov

erex

pose

d

Goe

s to

vap

or e

asy

87

SECT

ION

10

STA

BILI

TY A

ND

REA

CTIV

ITY

SECT

ION

11

TO

XICO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

12

ECO

LOG

ICAL

IN

FOR

MAT

ION

SECT

ION

13

DIS

POSA

L CO

NSI

DER

ATIO

NS

SECT

ION

14

TR

ANSP

ORT

INFO

RM

ATIO

N

SECT

ION

15

REG

ULA

TOR

Y IN

FOR

MAT

ION

SECT

ION

16

OTH

ER IN

FOR

MAT

ION

MSD

Srsquos

have

an

abun

danc

e of

in

form

atio

n us

eful

in

man

y di

ffer

ent

aspe

cts

88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

44 Each team shall identify a ldquomentorrdquo A mentor is defined as an adult who is included as a team member who will be supporting the team (or multiple teams) throughout the project year and may or may not be affiliated with the school institution or organization The mentor shall be certified by the National

Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and the rocketeer shall have flown and successfully recovered (using electronic staged recovery) a minimum of 2 flights in this or a higher impulse class prior to PDR The mentor is designated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site One travel stipend will be provided per mentor regardless of the number of teams he or she supports The stipend will only be provided if the team passes FRR and the team and

mentor attend launch week in April

45 During test flights teams shall abide by the rules and guidance of the local rocketry clubrsquos RSO The allowance of certain vehicle configurations andor payloads at the NASA University Student Launch Initiative competition launch does not give explicit or implicit authority for teams to fly those certain vehicle configurations andor payloads at other club launches Teams should communicate their

intentions to the local clubrsquos President or Prefect and RSO before attending any NAR or TRA launch

46 Teams shall abide by all rules and regulations set forth by the FAA

5 General Requirements 51 Team members (students if the team is from an academic institution) shall do 100 of the project

including design construction written reports presentations and flight preparation The one exception deals with the handling of black powder ejection charges and installing electric matches These tasks

shall be performed by the teamrsquos mentor regardless if the team is from an academic institution or not

52 The team shall provide and maintain a project plan to include but not limited to the following items project milestones budget and community support checklists personnel assigned educational engagement events and risks and mitigations

53 Each team shall successfully complete and pass a review in order to move onto the next phase of the competition

54 Foreign National (FN) team members shall be identified by the Preliminary Design Review (PDR) and may or may not have access to certain activities during launch week due to security restrictions In addition FNrsquos will be separated from their team during these activities If participating in the MAV task less than 50 of the team make-up may be foreign nationals

55 The team shall identify all team members attending launch week activities by the Critical Design Review

(CDR) Team members shall include

551 Students actively engaged in the project throughout the entirety of the project lifespan and currently enrolled in the proposing institution

552One mentor (see requirement 44) 553No more than two adult educators per academic team

56 The team shall engage a minimum of 200 participants in educational hands-on science technology engineering and mathematics (STEM) activities as defined in the Educational Engagement form by FRR An educational engagement form shall be completed and submitted within two weeks after completion of each event A sample of the educational engagement form can be found in the handbook

57 The team shall develop and host a Website for project documentation

10

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

NAS

A Pr

ojec

t Life

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uxili

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ojec

t Life

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42

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r Lau

nch

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redi

ctio

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pera

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Inte

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the

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tern

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erifi

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ntifi

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44

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Che

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ts

45

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iew

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erifi

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hicl

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uire

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ts V

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ort E

quip

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Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

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ffec

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Mit

igat

ion

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ific

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Haz

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61

Haz

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faci

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2

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A

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Max

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unt

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320

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41

1E

Foa

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re

duri

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stin

g

Tes

t req

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gh

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Byp

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ve

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eva

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dust

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Hyg

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pe

rson

nel a

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ven

tilat

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requ

irem

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f 10

min

utes

with

the

cham

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300

cfm

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rovi

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noug

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304

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whi

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equi

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min

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10

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re a

llow

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to e

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ally

if

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abno

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are

ob

serv

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dust

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e ca

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to p

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air

sa

mpl

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1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

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f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

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D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

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TO

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FOR

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ION

13

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L CO

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ION

14

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ORT

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ATIO

N

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ION

15

REG

ULA

TOR

Y IN

FOR

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ION

SECT

ION

16

OTH

ER IN

FOR

MAT

ION

MSD

Srsquos

have

an

abun

danc

e of

in

form

atio

n us

eful

in

man

y di

ffer

ent

aspe

cts

88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

58 Teams shall post and make available for download the required deliverables to the team Web site by the due dates specified in the project timeline

59 All deliverables must be in PDF format

510In every report teams shall provide a table of contents including major sections and their respective sub-sections

511In every report the team shall include the page number at the bottom of the page

512The team shall provide any computer equipment necessary to perform a video teleconference with the

review board This includes but not limited to computer system video camera speaker telephone and a broadband Internet connection If possible the team shall refrain from use of cellular phones as a means of speakerphone capability

513Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and

Information Technology (EIT) Accessibility Standards (36 CFR Part 1194) Subpart B-Technical Standards (httpwwwsection508gov)

119421 Software applications and operating systems

119422 Web-based intranet and Internet information and applications

11

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

NAS

A Pr

ojec

t Life

Cyc

le

Char

les P

ierc

eDe

puty

Chi

ef S

pace

craf

t amp A

uxili

ary

Prop

ulsio

n Sy

stem

s Bra

nch

NAS

A -M

arsh

all S

pace

Flig

ht C

ente

r

39

Topi

cs

bullPu

rpos

e O

bjec

tive

bullPr

ojec

t Life

Cyc

lebull

Syst

em R

equi

rem

ents

Rev

iew

(NA

to N

ASA

Stud

ent L

aunc

h)bull

Prel

imin

ary

Desig

nbull

Criti

cal (

Fina

l) De

sign

bullFl

ight

Rea

dine

ss

40

Purp

ose

Obj

ectiv

es

of th

e N

ASA

Proj

ect L

ife C

ycle

bullPl

an fo

r the

des

ign

bui

ld v

erifi

catio

n fl

ight

op

erat

ions

and

disp

osal

of t

he d

esire

d sy

stem

bullM

aint

ain

cons

isten

cy b

etw

een

proj

ects

bullSe

t exp

ecta

tions

for P

roje

ct M

anag

ers

and

Syst

em E

ngin

eers

ndashPl

ans a

nd D

eliv

erab

les

ndashFi

delit

yndash

Tim

ing

41

Typi

cal N

ASA

Proj

ect L

ife C

ycle

Refe

renc

e N

PR 71

205

D F

igur

e 2-

4 ldquo

The

NAS

A Pr

ojec

t Life

Cyc

lerdquo

42

Stud

ent L

aunc

h Pr

ojec

ts L

ife C

ycle

Phas

e A

Phas

e B

Phas

e C

Phas

e D

Phas

e E

Phas

e F

Acqu

isiti

on amp

Pr

elim

inar

y De

sign

Fina

l Des

ign

Fabr

icat

ion

amp

Ope

ratio

ns amp

Di

spos

alRe

quire

men

tsLa

unch

Sust

ainm

ent

Auth

ority

to P

roce

edSR

RPD

RCD

RFR

R Laun

chbull

ATP

(Aut

horit

y to

Proc

eed)

ndashFu

ndin

g is

appl

ied

to th

e co

ntra

cte

ffort

and

wor

k per

form

ance

ca

n be

gin

bullSR

R (S

yste

m R

equi

rem

ents

Rev

iew

) ndashTo

p Le

vel R

equi

rem

ents

are

conv

erte

d in

to sy

stem

re

quire

men

ts S

yste

m R

equi

rem

ents

are

revi

ewed

and

aut

horit

y is g

iven

to p

roce

ed in

to

Prel

imin

ary

Desig

n T

he N

ASA

Stud

ent L

aunc

h Pr

ojec

t ski

ps th

is st

ep

bullPD

R (P

relim

inar

y Des

ign

Revi

ew) ndash

Prel

imin

ary

Desig

n is

revi

ewed

and

aut

horit

y is g

iven

to

proc

eed

into

Fin

al D

esig

nbull

CDR

(Crit

ical

Des

ign

Revi

ew) ndash

Fina

l Des

ign

is re

view

ed a

nd a

utho

rity i

s giv

en to

pro

ceed

to

build

the

syst

em

bullFR

R (F

light

Rea

dine

ss R

evie

w) ndash

As-b

uilt

desig

n an

d te

st d

ata

are

revi

ewed

and

aut

horit

y is

give

n fo

r Lau

nch

43

Prel

imin

ary

Desi

gn R

evie

wbull

Obj

ectiv

endash

Prov

e th

e fe

asib

ility

to b

uild

and

laun

ch th

e ro

cket

pay

load

des

ign

ndash

Prov

e th

at a

ll sy

stem

requ

irem

ents

will

be

met

ndash

Rece

ive

auth

ority

to p

roce

ed to

the

Fina

l Des

ign

Phas

ebull

Typi

cal P

rodu

cts (

Vehi

cle

and

Payl

oad)

ndashSc

hedu

le (d

esig

n b

uild

tes

t)ndash

Cost

Bud

get S

tate

men

tndash

Prel

imin

ary

Desig

n Di

scus

sion

bullDr

awin

gs s

ketc

hes

bullId

entif

icatio

n an

d di

scus

sion

of co

mpo

nent

sbull

Anal

yses

(suc

h as

Veh

icle

Traj

ecto

ry P

redi

ctio

ns)

bullRi

sks

bullM

ass S

tate

men

t and

Mas

s Mar

gin

ndashM

issio

n Pr

ofile

(Con

cept

of O

pera

tions

)ndash

Inte

rfac

es (w

ithin

the

syst

em an

d ex

tern

al to

the

syst

em)

ndashTe

st a

nd V

erifi

catio

n Pl

anndash

Gro

und

Supp

ort E

quip

men

t Des

igns

Ide

ntifi

catio

nndash

Safe

ty F

eatu

res

44

Criti

cal D

esig

n Re

view

bullO

bjec

tive

ndashCo

mpl

ete

the

final

des

ign

of th

e ro

cket

pay

load

sys

tem

ndashRe

ceiv

e au

thor

ity to

pro

ceed

into

Fab

ricat

ion

and

Verif

icat

ion

phas

e

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

PDR

Deliv

erab

les

(mat

ured

to re

flect

the

final

des

ign)

ndashRe

port

and

dis

cuss

com

plet

ed te

sts

ndashPr

oced

ures

and

Che

cklis

ts

45

Flig

ht R

eadi

ness

Rev

iew

bullO

bjec

tive

ndashPr

ove

that

the

Rock

etP

aylo

ad Sy

stem

has

bee

n fu

lly b

uilt

test

ed a

nd v

erifi

ed

to m

eet t

he sy

stem

requ

irem

ents

ndashPr

ove

that

all

syst

em re

quire

men

ts h

ave

been

or w

ill b

e m

etndash

Rece

ive

auth

ority

to La

unch

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

Sche

dule

ndashCo

st S

tate

men

tndash

Desig

n O

verv

iew

bullKe

y com

pone

nts

bullKe

y dra

win

gs an

d la

yout

sbull

Traj

ecto

ry an

d ot

her k

ey a

naly

ses

bullM

ass S

tate

men

t bull

Rem

aini

ng R

isks

ndashM

issio

n Pr

ofile

ndash

Pres

enta

tion

and

anal

ysis

of te

st d

ata

ndashSy

stem

Req

uire

men

ts V

erifi

catio

nndash

Gro

und

Supp

ort E

quip

men

t ndash

Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

ause

E

ffec

t P

re-

RA

C

Mit

igat

ion

Ver

ific

atio

n P

ost-

RA

C

Per

sonn

el

expo

sure

to

high

vol

tage

Con

tact

with

en

ergi

zed

lam

p ba

nk c

ircu

its

Dea

th o

r se

vere

pe

rson

nel i

njur

y 1C

1

D

urin

g te

st o

pera

tion

lam

p ba

nks

circ

uits

will

be

ener

gize

d on

ly w

hen

no

pers

onne

l are

insi

de c

ham

ber

2

D

oor

to c

ham

ber

wil

l be

clos

ed

prio

r to

ene

rgiz

ing

circ

uits

3

T

S30

0 ac

cess

con

trol

s ar

e in

pl

ace

for

the

test

1

304-

TC

P-0

16 S

ectio

n 3

13

requ

ires

di

sabl

ing

heat

er e

lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r 2

P

er 3

04-T

CP

-016

tes

ts w

ill o

nly

be

perf

orm

ed u

nder

per

sona

l dir

ectio

n of

Tes

t E

ngin

eer

3

Acc

ess

cont

rols

for

this

test

are

in

clud

ed in

304

-TC

P-0

16 T

hese

incl

ude

o

L

ower

Eas

t Tes

t Are

a G

ate

6 a

nd T

urn

C6

Lig

ht to

RE

D

o

Low

er E

ast T

est A

rea

Gat

e 7

and

Tur

n C

7 L

ight

to R

ED

o

L

ower

Eas

t Tes

t Are

a G

ate

8 a

nd T

urn

C8

Lig

ht to

RE

D

o

Ver

ify

all G

over

nmen

t spo

nsor

ed v

ehic

les

are

clea

r of

the

area

o

V

erif

y al

l non

-Gov

ernm

ent s

pons

ored

ve

hicl

es a

re c

lear

of

the

area

o

M

ake

the

follo

win

g an

noun

cem

ent

ldquoAtte

ntio

n al

l per

sonn

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est o

pera

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ar

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out t

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t for

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rem

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Per

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le

ener

gize

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Acc

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tal

cont

act w

ith

lam

p or

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libra

tion

plat

e w

hile

out

Per

sonn

el b

urns

re

quir

ing

med

ical

tr

eatm

ent

3C

1

Dur

ing

test

ope

rati

on l

amp

bank

s ci

rcui

ts w

ill b

e en

ergi

zed

only

whe

n no

pe

rson

nel a

re in

side

cha

mbe

r

2

Doo

r to

cha

mbe

r w

ill c

lose

d pr

ior

to e

nerg

izin

g ci

rcui

ts

3

De s

igna

ted

pers

onne

l will

wea

r

leat

her

glov

es to

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dle

calib

ratio

n pl

ate

if r

equi

red

1

304-

TC

P-0

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13

requ

ires

di

sabl

ing

heat

er e

lect

rica

l cir

cuit

bef

ore

ente

ring

cha

mbe

r

2

Per

304

-TC

P-0

16 t

ests

wil

l onl

y be

pe

rfor

med

und

er p

erso

nal d

irec

tion

of T

est

Eng

inee

r 3

30

4-T

CP

-16

Sec

tion

14

Haz

ards

and

C

ontr

ols

req

uire

s in

sula

ted

glov

es a

s re

quir

ed

if h

ot it

ems

need

to b

e ha

ndle

d

3E

61

Haz

ard

C

ause

E

ffec

t P

re-

RA

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Mit

igat

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Ver

ific

atio

n P

ost-

RA

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Fai

lure

of

pres

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sy

stem

s

Ove

r-pr

essu

riza

tion

Per

sonn

el in

jury

Equ

ipm

ent

dam

age

1C

1

TS

300

faci

lity

pres

sure

sys

tem

s ar

e ce

rtif

ied

2

P

er E

T10

test

eng

inee

r h

igh

puri

ty a

ir s

yste

m w

ill b

e us

ed a

t lt 1

50

psig

ope

rati

ng p

ress

ure

ther

efor

e ce

rtif

icat

ion

not r

equi

red

3

A

ll n

on-c

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fied

test

equ

ipm

ent i

s pn

eum

atic

ally

pre

ssur

e te

sted

to 1

50

of

Max

imum

All

owab

le W

orki

ng P

ress

ure

(MA

WP

)

1

Per

the

MS

FC

Pre

ssur

e S

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ms

Rep

ortin

g T

ool (

PS

RT

) f

acili

ty s

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ms

have

be

en r

ecer

tifie

d un

der

TL

WT

-CE

RT

-10-

TS

300-

RR

2002

unt

il 3

320

20 T

he

cert

ific

atio

n in

clud

es G

aseo

us H

eliu

m G

aseo

us

Hyd

roge

n G

aseo

us N

itro

gen

Hig

h Pu

rity

Air

L

iqui

d H

ydro

gen

and

Liq

uid

Nitr

ogen

sys

tem

s

2

304-

TC

P-0

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tep

21

14 r

equi

res

HO

R-1

2-12

8 2

nd S

tage

HP

Air

HO

R t

o be

L

oade

d to

75p

sig

3

S

ee P

ress

ure

Tes

t Rep

ort P

TR

-001

455

(App

endi

x A

) A

ll no

n-ce

rtif

ied

equi

pmen

t has

a

min

imum

fac

tor

of s

afet

y of

41

1E

Foa

m p

anel

ca

tche

s fi

re

duri

ng te

stin

g

Tes

t req

uire

s hi

gh

heat

wit

h po

ssib

ility

of

pane

l bu

rnin

g

Rel

ease

of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

ion

requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

hed

Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

s so

ver

y lit

tle

or n

o re

sidu

al g

asse

s or

vap

ors

rem

ain

1

A m

inim

um v

enti

lati

on o

f th

e ch

ambe

r sh

ould

the

foam

pan

el b

urn

duri

ng o

r af

ter

test

ing

has

been

est

ablis

hed

by p

roce

dure

304

-T

CP

-016

whi

ch r

equi

res

the

min

imum

10

min

ute

vent

ilatio

n be

fore

per

sonn

el a

re a

llow

ed

to e

nter

Add

ition

ally

if

any

abno

rmal

ities

are

ob

serv

ed th

e In

dust

rial

Hea

lth r

epre

sent

ativ

e w

ill b

e ca

lled

to p

erfo

rm a

dditi

onal

air

sa

mpl

ing

befo

re p

erso

nnel

ent

ry

1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26

Proposal Requirements

At a minimum the proposing team shall identify the following in a written proposal due to NASA MSFC by the dates specified in the project timeline

General Information

1 A cover page that includes the name of the collegeuniversity or non-academic organization mailing address title of the project the date and which payload option(s) the team is participating in

2 Name title and contact information for up to two adult educators (for academic teams)

3 Name and title of the individual who will take responsibility for implementation of the safety plan (Safety Officer)

4 Name title and contact information for the team leader

5 Approximate number of participants who will be committed to the project and their proposed duties Include an outline of the project organization that identifies the key managers (participants andor educator administrators) and the key technical personnel Only use first names for identifying team members do not include surnames (See requirement 54 and 55 for definition of team members)

6 Name of the NARTRA section(s) the team is planning to work with for purposes of mentoring review of designs and documentation andor launch assistance

FacilitiesEquipment 1 Description of facilities and hours of accessibility necessary personnel equipment and supplies that are

required to design and build a rocket and the payload

Safety The Federal Aviation Administration (FAA) [wwwfaagov] has specific laws governing the use of airspace A

demonstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use of airspace at the launch sites and the use of combustible flammable material) safety codes guidelines and procedures for building testing and flying large model rockets is crucial The procedures and safety regulations of the NAR [httpwwwnarorgsafetyhtml] shall be used for flight design and operations The NARTRA mentor and Safety Officer shall oversee launch operations and motor handling

1 Provide a written safety plan addressing the safety of the materials used facilities involved and team

member responsible ie Safety Officer for ensuring that the plan is followed A risk assessment should be done for all aspects in addition to proposed mitigations Identification of risks to the successful completion of the project should be included

11 Provide a description of the procedures for NARTRA personnel to perform Ensure the following

Compliance with NAR high power safety code requirements [httpnarorgNARhpschtml]

Performance of all hazardous materials handling and hazardous operations

12 Describe the plan for briefing team members on hazard recognition and accident avoidance and conducting pre-launch briefings

13 Describe methods to include necessary caution statements in plans procedures and other working documents including the use of proper Personal Protective Equipment (PPE)

12

14 Provide a plan for complying with federal state and local laws regarding unmanned rocket launches and motor handling Specifically regarding the use of airspace Federal Aviation Regulations 14 CFR Subchapter F Part 101 Subpart C Amateur Rockets Code of Federal Regulation 27 Part 55

Commerce in Explosives and fire prevention NFPA 1127 ldquoCode for High Power Rocket Motorsrdquo

15 Provide a plan for NRATRA mentor purchase storage transport and use of rocket motors and energetic devices

16 Provide a written statement that all team members understand and will abide by the following safety regulations 161 Range safety inspections of each rocket before it is flown Each team shall comply with the

determination of the safety inspection or may be removed from the program

162 The RSO has the final say on all rocket safety issues Therefore the RSO has the right to deny the launch of any rocket for safety reasons

163 Any team that does not comply with the safety requirements will not be allowed to launch their rocket

Technical Design 1 A proposed and detailed approach to rocket and payload design

a Include general vehicle dimensions material selection and justification and construction methods

b Include projected altitude and describe how it was calculated c Include projected parachute system design d Include projected motor brand and designation

e Include description of the teamrsquos projected payload f Address the requirements for the vehicle recovery system and payload g Address major technical challenges and solutions

Educational Engagement 1 Include plans and evaluation criteria for required educational engagement activities (See requirement 55)

Project Plan 1 Provide a detailed development scheduletimeline covering all aspects necessary to successfully

complete the project

2 Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch week

3 Provide a detailed funding plan

4 Provide a written plan for soliciting additional ldquocommunity supportrdquo which could include but is not limited to expertise needed additional equipmentsupplies sponsorship services (such as free shipping for launch vehicle components if required advertisement of the event etc) or partnering with industry or other public or private schools

5 Develop a clear plan for sustainability of the rocket project in the local area This plan should include how to provide and maintain established partnerships and regularly engage successive teams in rocketry It should also include partners (industrycommunity) recruitment of team members funding sustainability and educational engagement

13

Prior to award all proposing entities may be required to brief NASA representatives The NASA MSFC Academic Affairs Office will determine the time and the place for the briefings Deliverables shall include 1 A reusable rocket and required payload ready for the official launch

2 A scale model of the rocket design with a payload prototype This model should be flown prior to the CDR A report of the data from the flight and the model should be brought to the CDR

3 Reports PDF slideshows and Milestone Review Flysheets due according to the provided timeline and shall be posted on the team Web site by the due date (Dates are tentative at this point Final dates will be announced at the time of award)

4 The team(s) shall have a Web presence no later than the date specified The Web site shall be maintained updated throughout the period of performance

5 Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event

The team shall participate in a PDR CDR FRR LRR and PLAR (Dates are tentative and subject to change)

The PDR CDR FRR and LRR will be presented to NASA at a time andor location to be determined by NASA MSFC Academic Affairs Office

14

VehiclePayload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk and within the cost and schedule constraints and establishes the basis for proceeding with detailed design It shows that the correct design options have been selected interfaces have been identified and verification methods have been described Full baseline cost and schedules as well as all risk assessment management systems and metrics are presented

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Preliminary Design Review Report

All information contained in the general information section of the project proposal shallalso be included in the PDR Report

I) Summary of PDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass

Motor choice Recovery system Milestone Review Flysheet

Payload Summary Payload title

Summarize payload experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes Changes made to vehicle criteria Changes made to payload criteria

Changes made to project plan

III) Vehicle Criteria

Selection Design and Verification of Launch Vehicle Include a mission statement requirements and mission success criteria Review the design at a system level going through each systemrsquos functional requirements (includes

sketches of options selection rationale selected concept and characteristics)

Describe the subsystems that are required to accomplish the overall mission Describe the performance characteristics for the system and subsystems and determine the evaluation

and verification metrics

16

Describe the verification plan and its status At a minimum a table should be included that lists each requirement (in SOW) and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection

analysis andor test)

Define the risks (time resource budget scopefunctionality etc) associated with the project Assign a likelihood and impact value to each risk Keep this part simple ie low medium high likelihood and low medium high impact Develop mitigation techniques for each risk Start with

the risks with higher likelihood and impact and work down from there If possible quantify the mitigation and impact For example including extra hardware to increase safety will have a quantifiable impact on budget Including this information in a table is highly encouraged

Demonstrate an understanding of all components needed to complete the project and how risksdelays impact the project

Demonstrate planning of manufacturing verification integration and operations (include component testing functional testing or static testing)

Describe the confidence and maturity of design Include a dimensional drawing of entire assembly The drawing set should include drawings of the entire

launch vehicle compartments within the launch vehicle (such as parachute bays payload bays and electronics bays) and significant structural design features of the launch vehicle (such as fins and bulkheads)

Include electrical schematics for the recovery system Include a Mass Statement Discuss the estimated mass of the launch vehicle its subsystems and

components What is the basis of the mass estimate and how accurate is it Discuss how much margin there is before the vehicle becomes too heavy to launch with the identified propulsion system Are you holding any mass in reserve (ie are you planning for any mass growth as the design matures) If so how much As a point of reference a reasonable rule of thumb is that the mass of a new product will grow between 25 and 33 between PDR and the delivery of the final product

Recovery Subsystem Demonstrate that analysis has begun to determine expected mass of launch vehicle and

parachute size attachment scheme deployment process and test resultsplans with ejection charges and electronics

Discuss the major components of the recovery system (such as the parachutes parachute harnesses attachment hardware and bulkheads) and verify that they will be robust enough to

withstand the expected loads

Mission Performance Predictions State mission performance criteria Show flight profile simulations altitude predictions with simulated vehicle data component weights

and simulated motor thrust curve and verify that they are robust enough to withstand the expected loads

Show stability margin simulated Center of Pressure (CP)Center of Gravity (CG) relationship and locations Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle Calculate the drift for each independent section of the launch vehicle from the launch pad for five

different cases no wind 5-mph wind 10-mph wind 15-mph wind and 20-mph wind The drift

calculations should be performed with the assumption that the rocket will be launched in the same direction as the wind

17

Interfaces and Integration Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle be compatible with stresses placed on the vehicle and integrate easily and simply

Describe the interfaces that are internal to the launch vehicle such as between compartments and subsystems of the launch vehicle

Describe the interfaces between the launch vehicle and the ground (mechanical electrical andor wirelesstransmitting)

Describe the interfaces between the launch vehicle and the ground launch system

Safety

Develop a preliminary checklist of final assembly and launch procedures

Identify a safety officer for your team Provide a preliminary Hazard analysis including hazards to personnel Also include the failure modes of

the proposed design of the rocket payload integration and launch operations Include proposed mitigations to all hazards (and verifications if any are implemented yet) Rank the risk of each Hazard

for both likelihood and severity

bull Include data indicating that the hazards have been researched (especially personnel)

Examples NAR regulations operatorrsquos manuals MSDS etc

Discuss any environmental concerns bull This should include how the vehicle affects the environment and how the environment can

affect the vehicle

IV) Payload Criteria

Selection Design and Verification of payload Review the design at a system level going through each systemrsquos functional requirements

(includes sketches of options selection rationale selected concept and characteristics)

Describe the payload subsystems that are required to accomplish the mission objectives Describe the performance characteristics for the system and subsystems and determine the

evaluation and verification metrics

Describe the verification plan and its status At a minimum a table should be included that lists each payload requirement and for each requirement briefly describe the design feature that will satisfy that requirement and how that requirement will ultimately be verified (such as by inspection analysis andor test)

Describe preliminary integration plan Determine the precision of instrumentation repeatability of measurement and recovery system

Include drawings and electrical schematics for the key elements of the payload Discuss the key components of the payload and how they will work together to achieve the

desired mission objectives

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives

State the payload success criteria Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls

18

Show relevance of expected data and accuracyerror analysis

Describe the preliminary experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must be completed before the next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation

Vehicle dimensions materials and justifications Static stability margin Plan for vehicle safety verification and testing

Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview

DrawingDiscussion of each major component and subsystem especially the recovery subsystem Baseline Payload design Payload verification and test plan overview

The PDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements has a high probability of meeting the mission objectives and can be safely constructed tested launched and recovered Upon successful completion of the PDR the team is given the authority to proceed into the final design phase of the life cycle that

will culminate in the Critical Design Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the PDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should use dark text on a light background

19

Critical Design Review (CDR) Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrication assembly integration and test that the technical effort is on track to complete the flight and ground

system development and mission operations in order to meet overall performance requirements within the identified cost schedule constraints Progress against management plans budget and schedule as well as risk assessment are presented The CDR is a review of the final design of the launch vehicle and payload system

All analyses should be complete and some critical testing should be complete The CDR Report and Presentation should be independent of the PDR Report and Presentation However the CDR Report and Presentation may have the same basic content and structure as the PDR documents but with final design information that may or

may not have changed since PDR Although there should be discussion of subscale models the CDR documents are to primarily discuss the final design of the full-scale launch vehicle and subsystems

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Critical Design Review Report

All information included in the general information sections of the project proposal andPDR shall be included

I) Summary of CDR report (1 page maximum)

Team Summary Team name and mailing address Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Motor choice

Recovery system Rail size Milestone Review Flysheet

Payload Summary Payload title

Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

20

III) Vehicle Criteria

Design and Verification of Launch Vehicle Flight Reliability and Confidence Include mission statement requirements and mission success criteria Include major milestone schedule (project initiation design manufacturing verification operations

and major reviews)

Review the design at a system level

Final drawings and specifications Final analysis and model results anchored to test data

Test description and results Final motor selection

Demonstrate that the design can meet all system level functional requirements For each requirement

state the design feature that satisfies that requirement and how that requirement has been or will be verified

Specify approach to workmanship as it relates to mission success

Discuss planned additional component functional or static testing Status and plans of remaining manufacturing and assembly

Discuss the integrity of design Suitability of shape and fin style for mission Proper use of materials in fins bulkheads and structural elements Proper assembly procedures proper attachment and alignment of elements solid connection

points and load paths

Sufficient motor mounting and retention

Status of verification Drawings of the launch vehicle subsystems and major components Include a Mass Statement Discuss the estimated mass of the final design and its subsystems

and components Discuss the basis and accuracy of the mass estimate the expected mass

growth between CDR and the delivery of the final product and the sensitivity of the launch vehicle to mass growth (eg How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system)

Discuss the safety and failure analysis

Subscale Flight Results Include actual flight data from onboard computers if available

Compare the predicted flight model to the actual flight data Discuss the results Discuss how the subscale flight data has impacted the design of the full-scale launch vehicle

Recovery Subsystem Describe the parachute harnesses bulkheads and attachment hardware Discuss the electrical components and how they will work together to safely recover the launch vehicle

Include drawingssketches block diagrams and electrical schematics Discuss the kinetic energy at significant phases of the mission especially at landing Discuss test results Discuss safety and failure analysis

21

Mission Performance Predictions State the mission performance criteria Show flight profile simulations altitude predictions with final vehicle design weights and actual

motor thrust curve

Show thoroughness and validity of analysis drag assessment and scale modeling results

Show stability margin and the actual CP and CG relationship and locations

Payload Integration Ease of integration Describe integration plan Compatibility of elements

Simplicity of integration procedure Discuss any changes in the payload resulting from the subscale test

Launch concerns and operation procedures Submit a draft of final assembly and launch procedures including

Recovery preparation

Motor preparation Setup on launcher Igniter installation

Troubleshooting Post-flight inspection

Safety and Environment (Vehicle and Payload) Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations including proposed and completed mitigations

Update the listing of personnel hazards and data demonstrating that safety hazards have been researched such as material safety data sheets operatorrsquos manuals and NAR regulations and that hazard mitigations have been addressed and enacted

Discuss any environmental concerns This should include how the vehicle affects the environment and how the environment can affect

the vehicle

IV) Payload Criteria

Testing and Design of Payload Equipment Review the design at a system level

Drawings and specifications

Analysis results Test results Integrity of design

Demonstrate that the design can meet all system-level functional requirements Specify approach to workmanship as it relates to mission success Discuss planned component testing functional testing or static testing

Status and plans of remaining manufacturing and assembly Describe integration plan Discuss the precision of instrumentation and repeatability of measurement

22

Discuss the payload electronics with special attention given to safety switches and indicators

Drawings and schematics Block diagrams

Batteriespower Switch and indicator wattage and location Test plans

Provide a safety and failure analysis

Payload Concept Features and Definition Creativity and originality Uniqueness or significance Suitable level of challenge

Science Value Describe payload objectives State the payload success criteria

Describe the experimental logic approach and method of investigation Describe test and measurement variables and controls Show relevance of expected data and accuracyerror analysis

Describe the experiment process procedures

V) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the

next phase of the project can begin

Educational engagement plan and status

VI) Conclusion

23

Critical Design Review Presentation

Please include the following information in your presentation

Final launch vehicle and payload dimensions Discuss key design features

Final motor choice Rocket flight stability in static margin diagram Thrust-to-weight ratio and rail exit velocity

Mass Statement and mass margin Parachute sizes recovery harness type size length and descent rates Kinetic energy at key phases of the mission especially landing Predicted drift from the launch pad with 5- 10- 15- and 20-mph wind

Test plans and procedures Scale model flight test Tests of the staged recovery system

Final payload design overview Payload integration Interfaces (internal within the launch vehicle and external to the ground)

Status of requirements verification

The CDR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the final design of the launch vehicle (including the payload) showing that design meets the mission objectives and

requirements and that the design can be safety constructed tested launched and recovered Upon successful completion of the CDR the team is given the authority to proceed into the construction and verification phase of the life cycle which will culminate in a Flight Readiness Review

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the CDR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy-to-see slides appropriate placement of pictures graphs and videos professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

24

Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria

The FRR examines tests demonstrations analyses and audits that determine the overall system (all projects working together) readiness for a safe and successful flightlaunch and for subsequent flight operations of the as-

built rocket and payload system It also ensures that all flight and ground hardware software personnel and procedures are operationally ready

The panel will be expecting a professional and polished report It is advised to follow the order of sections as they appear below

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary Team name and mailing address

Name of mentor NARTRA number and certification level

Launch Vehicle Summary Size and mass Final motor choice Recovery system

Rail size Milestone Review Flysheet

Payload Summary Payload title Summarize the payload Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes

Changes made to vehicle criteria Changes made to Payload criteria

Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle Describe the design and construction of the launch vehicle with special attention to the features that will

enable the vehicle to be launched and recovered safely

Structural elements (such as airframe fins bulkheads attachment hardware etc) Electrical elements (wiring switches battery retention retention of avionics boards etc)

Drawings and schematics to describe the assembly of the vehicle

25

Discuss flight reliability confidence Demonstrate that the design can meet mission success criteria

Discuss analysis and component functional or static testing

Present test data and discuss analysis and component functional or static testing of components and subsystems

Describe the workmanship that will enable mission success Provide a safety and failure analysis including a table with failure modes causes effects and risk

mitigations

Discuss full-scale launch test results Present and discuss actual flight data Compare and contrast flight data to the predictions from analysis and simulations

Provide a Mass Report and the basis for the reported masses

Recovery Subsystem Describe and defend the robustness of as-built and as-tested recovery system

Structural elements (such as bulkheads harnesses attachment hardware etc) Electrical elements (such as altimeterscomputers switches connectors)

Redundancy features Parachute sizes and descent rates Drawings and schematics of the electrical and structural assemblies

Rocket-locating transmitters with a discussion of frequency wattage and range Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields (such as transmitters) This topic should also be included in the Safety and Failure Analysis section

Suitable parachute size for mass attachment scheme deployment process test results with ejection charge and electronics

Safety and failure analysis Include table with failure modes causes effects and risk mitigations

Mission Performance Predictions State mission performance criteria Provide flight profile simulations altitude predictions with real vehicle data component weights and

actual motor thrust curve Include real values with optimized design for altitude Include sensitivities

Thoroughness and validity of analysis drag assessment and scale modeling results Compare analyses and simulations to measured values from ground andor flight tests Discuss how the predictive analyses and simulation have been made more accurate by test and flight data

Provide stability margin with actual CP and CG relationship and locations Include dimensional moment diagram or derivation of values with points indicated on vehicle Include sensitivities

Discuss the management of kinetic energy through the various phases of the mission with special attention to landing

Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0- 5- 10- 15- and 20-mph It should be assumed that the rocket is launching in the same

direction as the wind

Verification (Vehicle) For each requirement (in SOW) describe how that requirement has been satisfied and by what method

the requirement was verified Note Design features of a product often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

26

Safety and Environment (Vehicle) Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a

table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle

Payload Integration Describe the integration of the payload into the launch vehicle Demonstrate compatibility of elements and show fit at interface dimensions Describe and justify payload-housing integrity

Demonstrate integration show a diagram of components and assembly with documented process

IV) Payload Criteria

Experiment Concept This concerns the quality of science Give clear concise and descriptive explanations Creativity and originality

Uniqueness or significance

Science Value Describe payload objectives in a concise and distinct manner State the mission success criteria Describe the experimental logic scientific approach and method of investigation

Explain how it is a meaningful test and measurement and explain variables and controls Discuss the relevance of expected data along with an accuracyerror analysis including tables and plots Provide detailed experiment process procedures

Payload Design Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements

Structural elements (such as airframe bulkheads attachment hardware etc)

Electrical elements (wiring switches battery retention retention of avionics boards etc) Drawings and schematics to describe the design and assembly of the payload

Provide information regarding the precision of instrumentation and repeatability of measurement

(include calibration with uncertainty)

Provide flight performance predictions (flight values integrated with detailed experiment

operations)

Specify approach to workmanship as it relates to mission success

Discuss the test and verification program

27

Verification For each payload requirement describe how that requirement has been satisfied and by what

method the requirement was verified Note Design features often satisfy requirements and one or more of the following methods usually verify requirements analysis inspection and test

The verification statement for each payload requirement should include results of the analysis inspection andor test which prove that the requirement has been properly verified

Safety and Environment (payload) This will describe all concerns research and solutions to safety issues related to the payload Provide a safety and mission assurance analysis Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes causes effects and mitigationscontrols put in place to minimize the occurrence or effect of the hazard or failure) Discuss likelihood and potential

consequences for the top 5 to 10 failures (most likely to occur andor worst consequences)

As the program is moving into the operational phase of the Life Cycle update the listing of personnel hazards including data demonstrating that safety hazards that will still exist after FRR Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible

Discuss any environmental concerns that still exist

V) Launch Operations Procedures

Checklist Provide detailed procedure and check lists for the following (as a minimum) Recovery preparation Motor preparation

Setup on launcher Igniter installation Launch procedure

Troubleshooting Post-flight inspection

Safety and Quality Assurance Provide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist

Include the following

Provide data demonstrating that risks are at acceptable levels

Provide risk assessment for the launch operations including proposed and completed mitigations Discuss environmental concerns Identify the individual that is responsible for maintaining safety quality and procedures checklists

VI) Project Plan

Show status of activities and schedule Budget plan (in as much detail as possible) Funding plan Timeline (in as much detail as possible) GANTT charts are encouraged with a discussion and

indication of the critical path The critical path is the sequence of events that must occur before the next phase of the project can begin

Educational Engagement plan and status

VII) Conclusion 28

Flight Readiness Review Presentation

Please include the following information in your presentation

Launch Vehicle and payload design and dimensions

Discuss key design features of the launch vehicle Motor description Rocket flight stability in static margin diagram

Launch thrust-to-weight ratio and rail exit velocity Mass statement Parachute sizes and descent rates

Kinetic energy at key phases of the mission especially at landing Predicted altitude of the launch vehicle with a 5- 10- 15- and 20-mph wind Predicted drift from the launch pad with a 5- 10- 15- and 20-mph wind Test plans and procedures

Full-scale flight test Present and discuss the actual flight test data Recovery system tests Summary of Requirements Verification (launch vehicle)

Payload design and dimensions Key design features of the launch vehicle Payload integration

Interfaces with ground systems Summary of requirements verification (payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists engineers safety experts education specialists and industry partners The team is expected to present and defend the as-built

launch vehicle (including the payload) showing that the launch vehicle meets all requirements and mission objectives and that the design can be safely launched and recovered Upon successful completion of the FRR the team is given the authority to proceed into the Launch and Operational phases of the life cycle

It is expected that the team participants deliver the report and answer all questions The mentor shall only provide support in the presentation

The presentation of the FRR shall be well prepared with a professional overall appearance This includes but is not limited to the following easy to see slides appropriate placement of pictures graphs and videos

professional appearance of the presenters speaking clearly and loudly looking into the camera referring to the slides not reading them and communicating to the panel in an appropriate and professional manner The slides should be made with dark text on a light background

29

Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR) our launch services provider These inspections are only open to team members and mentors These names were

submitted as part of your team list All rocketspayloads will undergo a detailed deconstructive hands-on inspection Your team should bring all components of the rocket and payload except for the motor black powder and e-matches Be able to present anchored flight predictions anchored drift predictions (15 mph crosswind) procedures and checklists and CP and CG with loaded motor marked on the airframe The rockets will be assessed for structural electrical integrity and safety features At a minimum all teams should have

An airframe prepared for flight with the exception of energetic materials Data from the previous flight A list of any flight anomalies that occurred on the previous full-scale flight and the mitigation actions

A list of any changes to the airframe since the last flight Flight simulations Pre-flight checklist and Fly Sheet

A ldquopunch listrdquo will be generated for each team Items identified on the punch list should be corrected and verified by launch servicesNASA prior to launch day A flight card will be provided to teams to be completed and provided at the RSO booth on launch day

Post-Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria

The PLAR is an assessment of system in-flight performance

The PLAR should include the following items at a minimum and be about 4-15 pages in length Team name

Motor used Brief payload description Vehicle Dimensions Altitude reached (Feet)

Vehicle Summary Data analysis amp results of vehicle Payload summary

Data analysis amp results of payload Scientific value Visual data observed

Lessons learned Summary of overall experience (what you attempted to do versus the results and how you felt your

results were how valuable you felt the experience was)

Educational Engagement summary

Budget Summary

30

Participantrsquos Grade Level

Education Outreach

Direct Interactions Indirect

Interactions Direct Interactions Indirect

Interactions

K‐4

5‐9

10‐12

12+

Educators (5‐9)

Educators (other)

Educational Engagement Form

Please complete and submit this form each time you host an educational engagement event (Return within 2 weeks of the event end date)

SchoolOrganization name

Date(s) of event

Location of event

Instructions for participant count

EducationDirect Interactions A count of participants in instructional hands‐on activities where participants engage in learning a STEM topic by actively participating in an activity This includes instructor‐ led facilitation around an activity regardless of media (eg DLN face‐to‐face downlinketc) Example Students learn about Newtonrsquos Laws through building and flying a rocket This type of interaction will count towards your requirement for the project

EducationIndirect Interactions A count of participants engaged in learning a STEM topic through instructor‐led facilitation or presentation Example Students learn about Newtonrsquos Laws through a PowerPoint presentation

OutreachDirect Interaction A count of participants who do not necessarily learn a STEM topic but are able to get a hands‐on look at STEM hardware For example team does a presentation to students about their Student Launch project brings their rocket and components to the event and flies a rocket at the end of the presentation

OutreachIndirect Interaction A count of participants that interact with the team For example The team sets up a display at the local museum during Science Night Students come by and talk to the team about their project

Grade level and number of participants (If you are able to break down the participants into grade levels PreK‐4 5‐9 10‐12 and 12+ this will be helpful)

Are the participants with a special grouporganization (ie Girl Scouts 4‐H school) Y N

If yes what grouporganization

31

Briefly describe your activities with this group

Did you conduct an evaluation If so what were the results

Describe the comprehensive feedback received

32

Safety

High Power Rocket Safety Code Provided by the National Association of Rocketry

1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing

2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket

3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will not allow smoking open flames nor heat sources within 25 feet of these motors

4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the ldquooffrdquo position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position

5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcherrsquos safety interlock or disconnect its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket

6 Launch Safety I will use a 5-second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of a problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127

7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motorrsquos exhaust from hitting the ground I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table and will increase this distance by a factor of 15 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant

8 Size My rocket will not contain any combination of motors that total more than 40960 N-sec (9208 pound-seconds) of total impulse My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch

9 Flight Safety I will not launch my rocket at targets into clouds near airplanes nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site

10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N-sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters (2000 feet)

34

11 Launcher Location My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site

12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame-resistant or fireproof recovery system wadding in my rocket

13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it is likely to recover in spectator areas or outside the launch site nor attempt to catch it as it approaches the ground

35

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft)

Minimum Personnel Distance (ft)

Minimum Personnel Distance (Complex Rocket) (ft)

0 ndash 32000 H or smaller 50 100 200

32001 ndash 64000 I 50 100 200

64001 ndash 128000 J 50 100 200

128001 ndash 256000

K 75 200 300

256001 ndash 512000

L 100 300 500

512001 ndash 1024000

M 125 500 1000

1024001 ndash 2048000

N 125 1000 1500

2048001 ndash 4096000

O 125 1500 2000

Minimum Distance Table

Note A Complex rocket is one that is multi-staged or that is propelled by two or more rocket motors Revision of July 2008

Provided by the National Association of Rocketry (wwwnarorg)

36

Related Documents

Award Award Description Determined by When awarded

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while sti ll maximizing safety and

efficiency USLI pane l Launch Week

Experiment Design Award

Awarded to the team with the most creative and innovative payload design whil e maximi zing safety and science val ue USLI pane l Launch Week

Safety Award Awarded to the team that demonstrates the highest level of safety

according to the scoring rubric USLI pane l Launch Week

Project Review (PDRCDRFRR)

Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations USLI pane l Launch Week

Educational Engagement

Award

Awarded to the team that is determi ned to have best inspired the study of rocketry and other science technology engineering and math (STEM)

related topics in their community This team not only presented a high number of activities to a large number of people but also delivered quality

activities to a wide range of audiences

USLI pane l Launch Week

Web Design Award Awarded to the team that has the best most efficient Web site with all

documentation posted on time USLI pane l Launch Week

Altitude Award Awarded to the team that achieves the best altitude score according to the

scoring rubric and requirement 12 USLI pane l Launch Week

Best Looking Rocket

Awarded to the team that is judged by their peers to have the ldquoBest Looking Rocketrdquo

Peers Launch Week

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Best Rocket Fair Display

Award

Awarded to the team that is judged by their peers to display the ldquoBest Team Spiritrdquo on launch day

Peers Launch Week

Rookie Award Awarded to the top overall rookie team using the same criteria as the

Overall Winner Award (Only given if the overall winner is not a rookie team)

USLI pane l May 11 2016

Overall Winner Awarded to the top overall team Design reviews outreach Web site safety and a successful flight will all factor into the Overall Winner USLI pane l May 11 2016

USLI Competition Awards

38

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t and

Mas

s Mar

gin

ndashM

issio

n Pr

ofile

(Con

cept

of O

pera

tions

)ndash

Inte

rfac

es (w

ithin

the

syst

em an

d ex

tern

al to

the

syst

em)

ndashTe

st a

nd V

erifi

catio

n Pl

anndash

Gro

und

Supp

ort E

quip

men

t Des

igns

Ide

ntifi

catio

nndash

Safe

ty F

eatu

res

44

Criti

cal D

esig

n Re

view

bullO

bjec

tive

ndashCo

mpl

ete

the

final

des

ign

of th

e ro

cket

pay

load

sys

tem

ndashRe

ceiv

e au

thor

ity to

pro

ceed

into

Fab

ricat

ion

and

Verif

icat

ion

phas

e

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

PDR

Deliv

erab

les

(mat

ured

to re

flect

the

final

des

ign)

ndashRe

port

and

dis

cuss

com

plet

ed te

sts

ndashPr

oced

ures

and

Che

cklis

ts

45

Flig

ht R

eadi

ness

Rev

iew

bullO

bjec

tive

ndashPr

ove

that

the

Rock

etP

aylo

ad Sy

stem

has

bee

n fu

lly b

uilt

test

ed a

nd v

erifi

ed

to m

eet t

he sy

stem

requ

irem

ents

ndashPr

ove

that

all

syst

em re

quire

men

ts h

ave

been

or w

ill b

e m

etndash

Rece

ive

auth

ority

to La

unch

bullTy

pica

l Pro

duct

s (Ve

hicl

e an

d Pa

yloa

d)ndash

Sche

dule

ndashCo

st S

tate

men

tndash

Desig

n O

verv

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bullKe

y com

pone

nts

bullKe

y dra

win

gs an

d la

yout

sbull

Traj

ecto

ry an

d ot

her k

ey a

naly

ses

bullM

ass S

tate

men

t bull

Rem

aini

ng R

isks

ndashM

issio

n Pr

ofile

ndash

Pres

enta

tion

and

anal

ysis

of te

st d

ata

ndashSy

stem

Req

uire

men

ts V

erifi

catio

nndash

Gro

und

Supp

ort E

quip

men

t ndash

Proc

edur

es an

d Ch

eck

List

s

46

Haza

rd A

naly

sis

Intr

oduc

tion

to m

anag

ing

Risk

47

Wha

t is a

Haz

ard

Put s

impl

y itrsquo

s an

outc

ome

that

will

hav

e an

ad

vers

e af

fect

on

you

you

r pro

ject

or t

he

envi

ronm

ent

A cl

assic

exa

mpl

e of

a H

azar

d is

a Fi

re o

r Exp

losio

nndash

A ha

zard

has

man

y pa

rts

all

of w

hich

pla

y in

to

how

we

cate

goriz

e it

and

how

we

resp

ond

ndashN

ot a

ll ha

zard

s are

life

thre

aten

ing

or h

ave

cata

stro

phic

out

com

es T

hey

can

be m

ore

beni

gn

like

cuts

and

bru

ises

fund

ing

issue

s o

r sch

edul

e se

tbac

ks

48

Haza

rd D

escr

iptio

n

A ha

zard

des

crip

tion

is co

mpo

sed

of 3

par

ts

1Ha

zard

ndashSo

met

imes

cal

led

the

Haza

rdou

s ev

ent

or in

itiat

ing

even

t2

Caus

e ndash

How

the

Haza

rd o

ccur

s S

omet

imes

ca

lled

the

mec

hani

sm3

Effe

ct ndash

The

outc

ome

Thi

s is w

hat y

ou a

re

wor

ried

abou

t hap

peni

ng if

the

Haza

rd

man

ifest

s

49

Exam

ple

Haza

rd D

escr

iptio

n

Chem

ical

bur

ns d

ue to

mish

andl

ing

or sp

illin

g Hy

droc

hlor

ic A

cid

resu

lts in

serio

us in

jury

to

pers

onne

l

Haza

rdCa

use

Effe

ct

50

Risk

Risk

is a

mea

sure

of h

ow m

uch

emph

asis

a ha

zard

war

rant

sRi

sk is

def

ined

by

2 fa

ctor

sbull

Like

lihoo

d ndash

The

chan

ce th

at th

e ha

zard

will

oc

cur

This

is us

ually

mea

sure

d qu

alita

tivel

y bu

t can

be

quan

tifie

d if

data

exi

sts

bullSe

verit

y ndashIf

the

haza

rd o

ccur

s ho

w b

ad w

ill it

be

51

Risk

Mat

rix E

xam

ple

(exc

erpt

from

NAS

A M

PR 8

715

15)

TAB

LE

CH

11

RA

C

Prob

abili

ty

Seve

rity

1C

atas

trop

hic

2C

ritic

al3

Mar

gina

l4

Neg

ligib

le

A ndash

Freq

uent

1A2A

3A4A

B ndash

Prob

able

1B2B

3B4B

C ndash

Occ

asio

nal

1C2C

3C4C

D ndash

Rem

ote

1D2D

3D4D

E -

Impr

obab

le1E

2E3E

4E

Tabl

e C

H1

2

RIS

K A

CC

EPTA

NC

E A

ND

MA

NA

GEM

ENT

APP

RO

VA

L LE

VEL

Seve

rity

-Pro

babi

lity

Acc

epta

nce

Leve

lApp

rovi

ng A

utho

rity

Hig

h R

iskU

nacc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e M

SFC

EM

C o

r an

equ

ival

ent

leve

l in

depe

nden

t m

anag

emen

t co

mm

ittee

Med

ium

Risk

Und

esira

ble

D

ocum

ente

d ap

prov

al f

rom

the

faci

lity

oper

atio

n ow

nerrsquo

s D

epar

tmen

tLab

orat

ory

Off

ice

Man

ager

or d

esig

nee(

s) o

r an

equi

vale

nt l

evel

m

anag

emen

t co

mm

ittee

Low

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

fro

m th

e su

perv

isor

dire

ctly

res

pons

ible

for

op

erat

ing

the

faci

lity

or p

erfo

rmin

g th

e op

erat

ion

Min

imal

Risk

Acc

epta

ble

Doc

umen

ted

appr

oval

not

req

uire

d b

ut a

n in

form

al r

evie

w b

y th

e su

perv

isor

dire

ctly

res

pons

ible

for

ope

ratio

n th

e fa

cilit

y or

per

form

ing

the

oper

atio

n is

high

ly r

ecom

men

ded

U

se o

f a g

ener

ic J

HA

pos

ted

on th

e SH

E W

eb p

age

is re

com

men

ded

if

a ge

neric

JH

A h

as b

een

deve

lope

d

52

Risk

Con

tinue

d

Defin

ing

the

risk

on a

mat

rix h

elps

man

age

wha

t ha

zard

s ne

ed a

dditi

onal

wor

k a

nd w

hich

are

at

an a

ccep

tabl

e le

vel

Risk

shou

ld b

e as

sess

ed b

efor

e an

y co

ntro

ls or

m

itiga

ting

fact

ors a

re c

onsid

ered

AN

D af

ter

Upd

ate

risk

as y

ou im

plem

ent y

our s

afet

y co

ntro

ls

53

Miti

gatio

nsC

ontr

ols

Iden

tifyi

ng ri

sk is

nrsquot u

sefu

l if y

ou d

onrsquot

do th

ings

to

fix

itCo

ntro

lsm

itiga

tions

are

the

safe

ty p

lans

and

m

odifi

catio

ns y

ou m

ake

to re

duce

you

r risk

Ty

pes o

f Con

trol

sbull

Desig

nAn

alys

isTe

stbull

Proc

edur

esS

afet

y Pl

ans

bullPP

E (P

erso

nal P

rote

ctiv

e Eq

uipm

ent)

54

Verif

icat

ion

As y

ou p

rogr

ess t

hrou

gh th

e de

sign

revi

ew p

roce

ss

you

will

iden

tify m

any

way

s to

cont

rol y

our h

azar

ds

Even

tual

ly yo

u w

ill b

e re

quire

d to

ldquopro

verdquo t

hat t

he

cont

rols

you

iden

tify a

re va

lid T

his c

an b

e an

alys

is or

calc

ulat

ions

requ

ired

to sh

ow yo

u ha

ve st

ruct

ural

in

tegr

ity p

roce

dure

s to

laun

ch yo

ur ro

cket

or t

ests

to

valid

ate

your

mod

els

Verif

icat

ions

shou

ld b

e in

clud

ed in

your

repo

rts a

s th

ey b

ecom

e av

aila

ble

By

FRR

all v

erifi

catio

ns sh

all

be id

entif

ied

55

Exam

ple

Haza

rd A

naly

sis

In a

dditi

on to

this

hand

book

you

will

rece

ive

an

exam

ple

Haza

rd A

naly

sis T

he e

xam

ple

uses

a

mat

rix fo

rmat

for d

ispla

ying

the

Haza

rds

anal

yzed

Thi

s is n

ot re

quire

d b

ut it

typi

cally

m

akes

org

anizi

ng a

nd u

pdat

ing

your

ana

lysis

ea

sier

56

Safety Assessment Report (Hazard Analysis)

Hazard Analysis for the 12 ft Chamber IR Lamp Array - Foam Panel Ablation Testing

Prepared by Industrial Safety

Bastion Technologies Inc for

Safety amp Mission Assurance Directorate QD12 ndash Industrial Safety Branch

George C Marshall Space Flight Center

57

RAC CLASSIFICATIONS

The following tables and charts explain the Risk Assessment Codes (RACs) used to evaluate the hazards indentified in this report RACs are established for both the initial hazard that is before controls have been applied and the residualremaining risk that remains after the implementation of controls Additionally table 2 provides approvalacceptance levels for differing levels of remaining risk In all cases individual workers should be advised of the risk for each undertaking

TABLE 1 RAC

Probability Severity

1 2 3 4 Catastrophic Critical Marginal Negligible

A ndash Frequent 1A 2A 3A 4A B ndash Probable 1B 2B 3B 4B C ndash Occasional 1C 2C 3C 4C D ndash Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E

TABLE 2 Level of Risk and Level of Management Approval Level of Risk Level of Management ApprovalApproving Authority

High Risk Highly Undesirable Documented approval from the MSFC EMC or an equivalent level independent management committee

Moderate Risk Undesirable Documented approval from the facilityoperation ownerrsquos DepartmentLaboratoryOffice Manager or designee(s) or an equivalent level management committee

Low Risk Acceptable Documented approval from the supervisor directly responsible for operating the facility or performing the operation

Minimal Risk Acceptable Documented approval not required but an informal review by the supervisor directly responsible for operating the facility or performing the operation is highly recommended Use of a generic JHA posted on the SHE Webpage is recommended

58

TABLE 3 Severity Definitions ndash A condition that can cause Description Personnel

Safety and Health

FacilityEquipment Environmental

1 ndash Catastrophic Loss of life or a permanent-disabling injury

Loss of facility systems or associated hardware

Irreversible severe environmental damage that violates law and regulation

2 - Critical Severe injury or occupational-related illness

Major damage to facilities systems or equipment

Reversible environmental damage causing a violation of law or regulation

3 - Marginal Minor injury or occupational-related illness

Minor damage to facilities systems or equipment

Mitigatible environmental damage without violation of law or regulation where restoration activities can be accomplished

4 - Negligible First aid injury or occupational-related illness

Minimal damage to facility systems or equipment

Minimal environmental damage not violating law or regulation

TABLE 4 Probability Definitions Description Qualitative Definition Quantitative Definition A - Frequent High likelihood to occur immediately or Probability is gt 01

expected to be continuously experienced

B - Probable Likely to occur to expected to occur 01ge Probability gt 001 frequently within time

C - Occasional Expected to occur several times or 001 ge Probability gt 0001 occasionally within time

D - Remote Unlikely to occur but can be reasonably 0001ge Probability gt expected to occur at some point within 0000001 time

E - Improbable Very unlikely to occur and an occurrence 0000001ge Probability is not expected to be experienced within time

59

Haz

ard

C

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Dur

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Haz

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C

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Mit

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stem

s

Ove

r-pr

essu

riza

tion

Per

sonn

el in

jury

Equ

ipm

ent

dam

age

1C

1

TS

300

faci

lity

pres

sure

sys

tem

s ar

e ce

rtif

ied

2

P

er E

T10

test

eng

inee

r h

igh

puri

ty a

ir s

yste

m w

ill b

e us

ed a

t lt 1

50

psig

ope

rati

ng p

ress

ure

ther

efor

e ce

rtif

icat

ion

not r

equi

red

3

A

ll n

on-c

erti

fied

test

equ

ipm

ent i

s pn

eum

atic

ally

pre

ssur

e te

sted

to 1

50

of

Max

imum

All

owab

le W

orki

ng P

ress

ure

(MA

WP

)

1

Per

the

MS

FC

Pre

ssur

e S

yste

ms

Rep

ortin

g T

ool (

PS

RT

) f

acili

ty s

yste

ms

have

be

en r

ecer

tifie

d un

der

TL

WT

-CE

RT

-10-

TS

300-

RR

2002

unt

il 3

320

20 T

he

cert

ific

atio

n in

clud

es G

aseo

us H

eliu

m G

aseo

us

Hyd

roge

n G

aseo

us N

itro

gen

Hig

h Pu

rity

Air

L

iqui

d H

ydro

gen

and

Liq

uid

Nitr

ogen

sys

tem

s

2

304-

TC

P-0

16 S

tep

21

14 r

equi

res

HO

R-1

2-12

8 2

nd S

tage

HP

Air

HO

R t

o be

L

oade

d to

75p

sig

3

S

ee P

ress

ure

Tes

t Rep

ort P

TR

-001

455

(App

endi

x A

) A

ll no

n-ce

rtif

ied

equi

pmen

t has

a

min

imum

fac

tor

of s

afet

y of

41

1E

Foa

m p

anel

ca

tche

s fi

re

duri

ng te

stin

g

Tes

t req

uire

s hi

gh

heat

wit

h po

ssib

ility

of

pane

l bu

rnin

g

Rel

ease

of

haza

rds

mat

eria

ls in

to te

st

cham

ber

1C

1

Byp

rodu

cts

of c

ombu

stio

n ha

ve

been

eva

luat

ed b

y In

dust

rial

Hyg

iene

pe

rson

nel a

nd a

ven

tilat

ion

requ

irem

ent o

f 10

min

utes

with

the

cham

ber

300

cfm

ve

ntila

tion

fan

has

been

est

ablis

hed

Thi

s w

ill p

rovi

de e

noug

h ai

r ch

ange

s so

ver

y lit

tle

or n

o re

sidu

al g

asse

s or

vap

ors

rem

ain

1

A m

inim

um v

enti

lati

on o

f th

e ch

ambe

r sh

ould

the

foam

pan

el b

urn

duri

ng o

r af

ter

test

ing

has

been

est

ablis

hed

by p

roce

dure

304

-T

CP

-016

whi

ch r

equi

res

the

min

imum

10

min

ute

vent

ilatio

n be

fore

per

sonn

el a

re a

llow

ed

to e

nter

Add

ition

ally

if

any

abno

rmal

ities

are

ob

serv

ed th

e In

dust

rial

Hea

lth r

epre

sent

ativ

e w

ill b

e ca

lled

to p

erfo

rm a

dditi

onal

air

sa

mpl

ing

befo

re p

erso

nnel

ent

ry

1E

62

Und

erst

andi

ng

MS

DS

rsquos

By

Jef

f Mitc

hell

MS

FC E

nviro

nmen

tal H

ealth

63

Wha

t is

an M

SD

S

A

Mat

eria

l Saf

ety

Dat

a S

heet

(M

SD

S) i

s a

docu

men

t pr

oduc

ed b

y a

man

ufac

ture

r of

a

parti

cula

r ch

emic

al a

nd is

in

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

ow

to s

afel

y w

ork

with

or h

andl

e th

is

chem

ical

64

Wha

t is

an M

SD

S

M

SD

Srsquos

do

not h

ave

a st

anda

rd fo

rmat

bu

t the

y ar

e al

l req

uire

d to

hav

e ce

rtain

in

form

atio

n pe

r OS

HA

29

CFR

191

012

00

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

e re

quire

men

ts o

f thi

s O

SH

A s

tand

ard

in

diffe

rent

way

s

65

Req

uire

d da

ta fo

r MS

DS

rsquos

Id

entit

y of

haz

ardo

us c

hem

ical

C

hem

ical

and

com

mon

nam

es

Phy

sica

l and

che

mic

al c

hara

cter

istic

s

Phy

sica

l haz

ards

H

ealth

haz

ards

R

oute

s of

ent

ry

Exp

osur

e lim

its

66

Req

uire

d da

ta fo

r MSD

Srsquos

(Con

t)

C

arci

noge

nici

ty

Pro

cedu

res

for s

afe

hand

ling

and

use

C

ontro

l mea

sure

s

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

D

ate

of la

st M

SD

S u

pdat

e

Man

ufac

ture

rrsquos n

ame

add

ress

and

pho

ne

num

ber

67

Impo

rtant

Age

ncie

s

A

CG

IH

The

Amer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

h oc

cupa

tiona

l exp

osur

e lim

its fo

r man

y ch

emic

als

thes

e lim

its a

re c

alle

d TL

Vrsquos

(Thr

esho

ld L

imit

Valu

es)

68

Impo

rtant

Age

ncie

s (C

ont)

A

NS

I

The

Amer

ican

Nat

iona

l Sta

ndar

ds In

stitu

te is

a

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

at

rela

te t

o sa

fe d

esig

n an

d pe

rform

ance

of

equi

pmen

t an

d pr

actic

es

69

Impo

rtant

Age

ncie

s (C

ont)

N

FPA

Th

e N

atio

nal F

ire P

rote

ctio

n As

soci

atio

n

amon

g ot

her

thin

gs e

stab

lishe

d a

ratin

g sy

stem

use

d on

man

y la

bels

of h

azar

dous

ch

emic

als

calle

d th

e N

FPA

Dia

mon

d

The

NFP

A D

iam

ond

give

s co

ncis

e in

form

atio

n on

the

Hea

lth h

azar

d

Flam

mab

ility

haza

rd R

eact

ivity

haz

ard

and

Sp

ecia

l pre

caut

ions

An

exa

mpl

e of

the

NFP

A D

iam

ond

is o

n th

e ne

xt s

lide

70

NFP

A D

iam

ond

71

Impo

rtant

Age

ncie

s (C

ont)

N

IOS

H

The

Nat

iona

l Ins

titut

e of

Occ

upat

iona

l Saf

ety

and

Hea

lth is

an

agen

cy o

f the

Pub

lic H

ealth

Se

rvic

e th

at te

sts

and

certi

fies

resp

irato

ry a

nd

air

sam

plin

g de

vice

s I

t als

o in

vest

igat

es

inci

dent

s an

d re

sear

ches

occ

upat

iona

l saf

ety

72

Impo

rtant

Age

ncie

s (C

ont)

O

SH

A

The

Occ

upat

iona

l Saf

ety

and

Hea

lth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

e m

issi

on to

mak

e su

re th

at th

e sa

fety

and

he

alth

con

cern

s of

all

Amer

ican

wor

kers

are

be

ing

met

73

Exp

osur

e Li

mits

O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

P

erso

nnel

exp

osur

e ab

ove

the

expo

sure

lim

its is

not

con

side

red

safe

74

Exp

osur

e Li

mits

(Con

t)

O

SH

A c

alls

thei

r exp

osur

e lim

its P

ELrsquo

s

whi

ch s

tand

s fo

r Per

mis

sibl

e E

xpos

ure

Lim

it

OSH

A PE

Lrsquos

rare

ly c

hang

e

AC

GIH

est

ablis

hes

TLV

rsquos w

hich

sta

nds

for T

hres

hold

Lim

it V

alue

s

ACG

IH T

LVrsquos

are

upd

ated

ann

ually

75

Exp

osur

e Li

mits

(Con

t)

A

Cei

ling

limit

(not

ed b

y C

) is

a co

ncen

tratio

n th

at s

hall

neve

r be

ex

ceed

ed a

t any

tim

e

An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

th

at it

may

be

Imm

edia

tely

Dan

gero

us t

o Li

fe a

nd H

ealth

76

Exp

osur

e Li

mits

(Con

t)

A

STE

L is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

e ex

posu

re t

ime

A

TW

A i

s a

Tim

e W

eigh

ted

Ave

rage

and

is

use

d to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Che

mic

al a

nd P

hysi

cal P

rope

rties

B

oilin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om liq

uid

phas

e to

va

por p

hase

M

eltin

g P

oint

Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om s

olid

pha

se to

liq

uid

phas

e

Vap

or P

ress

ure

Th

e pr

essu

re o

f a v

apor

in e

quilib

rium

with

its

non-

vapo

r pha

ses

Mos

t of

ten

the

term

is u

sed

to d

escr

ibe

a liq

uidrsquo

s te

nden

cy to

eva

pora

te

Vap

or D

ensi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

vapo

r will

rise

or fa

ll in

air

V

isco

sity

It

is c

omm

only

perc

eive

d as

thi

ckne

ss

or re

sist

ance

to p

ourin

g A

hi

gher

vis

cosi

ty e

qual

s a

thic

ker l

iqui

d

78

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont)

S

peci

fic G

ravi

ty

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d wi

ll flo

at o

r sin

k in

wat

er

Sol

ubili

ty

This

is th

e am

ount

of a

sol

ute

that

will

diss

olve

in a

spe

cific

sol

vent

un

der g

iven

con

ditio

ns

Odo

r thr

esho

ld

The

lowe

st c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

Fl

ash

poin

t

The

lowe

st te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

U

pper

(UE

L) a

nd lo

wer

exp

losi

ve li

mits

(LE

L)

At c

once

ntra

tions

in a

ir be

low

the

LEL

ther

e is

not

eno

ugh

fuel

to

cont

inue

an

expl

osio

n a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

di

spla

ced

so m

uch

air t

hat t

here

is n

ot e

noug

h ox

ygen

to b

egin

a

reac

tion

79

Thin

gs y

ou s

houl

d le

arn

from

M

SDSrsquo

s

Is th

is c

hem

ical

haz

ardo

us

R

ead

the

Hea

lth H

azar

d se

ctio

n

Wha

t will

happ

en if

I am

exp

osed

Ther

e is

usu

ally

a s

ectio

n ca

lled

Sym

ptom

s of

E

xpos

ure

unde

r Hea

lth H

azar

d

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed

R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure

R

ead

Rou

tes

of E

ntry

Pro

cedu

res

for

safe

han

dlin

g an

d us

e a

nd C

ontro

l mea

sure

s

80

Take

you

r tim

e

S

ince

MS

DS

rsquos d

onrsquot

have

a s

tand

ard

form

at w

hat y

ou a

re s

eeki

ng m

ay n

ot b

e in

the

first

pla

ce y

ou lo

ok

Stu

dy y

our

MS

DS

rsquos b

efor

e th

ere

is a

pr

oble

m s

o yo

u ar

enrsquot

rush

ed

Rea

d th

e en

tire

MS

DS

bec

ause

in

form

atio

n in

one

loca

tion

may

co

mpl

imen

t inf

orm

atio

n in

ano

ther

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

milia

r with

this

che

mic

al

82

MSD

S M

ETH

YL E

THYL

KET

ON

E

SECT

ION

1 C

HEM

ICAL

PR

OD

UCT

AN

D C

OM

PAN

Y ID

ENTI

FICA

TIO

N

MD

L IN

FORM

ATIO

N S

YSTE

MS

IN

C14

600

CATA

LIN

A ST

REET

1-80

0-63

5-00

64 O

R1-

510-

895-

1313

FOR

EMER

GEN

CY S

OU

RCE

INFO

RMAT

ION

CON

TACT

1-

615-

366-

2000

USA

CAS

NU

MBE

R 7

8-93

-3RT

ECS

NU

MBE

R E

L647

5000

EU N

UM

BER

(EIN

ECS)

20

1-15

9-0

EU I

ND

EX N

UM

BER

606-

002-

00-3

SUBS

TAN

CE

MET

HYL

ETH

YL K

ETO

NE

TRAD

E N

AMES

SYN

ON

YMS

BUTA

NO

NE

2-B

UTA

NO

NE

ETH

YL M

ETH

YL K

ETO

NE

MET

HYL

ACE

TON

E 3

-BU

TAN

ON

E M

EK

SCO

TCH

-GRI

P reg

BRA

ND

SO

LVEN

T

3 (3

M)

STO

P S

HIE

LD P

EEL

RED

UCE

R (P

YRAM

IDPL

ASTI

CS I

NC

) S

TABO

ND

C-T

HIN

NER

(ST

ABO

ND

CO

RP)

O

ATEY

CLE

ANER

(O

ATEY

COM

PAN

Y)

RCRA

U15

9 U

N11

93

STCC

490

9243

C4H

8O

OH

S144

60

CHEM

ICAL

FAM

ILY

Keto

nes

alip

hatic

CREA

TIO

N D

ATE

Sep

28

1984

REVI

SIO

N D

ATE

Mar

30

1997

Last

rev

isio

n

Man

ufac

ture

r na

me

and

phon

e

Abbr

evia

ted

MSD

S

83

SECT

ION

2 C

OM

POSI

TIO

N I

NFO

RM

ATIO

N O

N I

NG

RED

IEN

TS

COM

PON

ENT

MET

HYL

ETH

YL K

ETO

NE

CAS

NU

MBE

R 7

8-93

-3PE

RCEN

TAG

E 1

00

SECT

ION

3 H

AZAR

DS

IDEN

TIFI

CATI

ON

NFP

A RA

TIN

GS

(SCA

LE 0

-4)

Hea

lth=

2 F

ire=

3 R

eact

ivity

=0

EMER

GEN

CY O

VERV

IEW

CO

LOR

col

orle

ssPH

YSIC

AL F

ORM

liq

uid

OD

OR

min

ty s

wee

t odo

rM

AJO

R H

EALT

H H

AZAR

DS

resp

irato

ry t

ract

irrit

atio

n s

kin

irrita

tion

eye

irrita

tion

cen

tral

ner

vous

sys

tem

dep

ress

ion

PHYS

ICAL

HAZ

ARD

S F

lam

mab

le li

quid

and

vap

or V

apor

may

cau

se fl

ash

fire

Goo

d in

fo fo

rla

belin

g co

ntai

ners

23

0

POTE

NTI

AL H

EALT

H E

FFEC

TS

INH

ALAT

ION

SH

ORT

TER

M E

XPO

SURE

irr

itatio

n n

ause

a v

omiti

ng d

iffic

ulty

bre

athi

ng

Wha

t hap

pens

whe

n ex

pose

d

84

SKIN

CO

NTA

CT

SHO

RT T

ERM

EXP

OSU

RE i

rrita

tion

LON

G T

ERM

EXP

OSU

RE s

ame

as e

ffect

s re

port

ed in

sho

rt t

erm

exp

osur

eEY

E CO

NTA

CThellip

ING

ESTI

ON

hellip

CARC

INO

GEN

STA

TUS

OSH

A N

NTP

NIA

RC N

SECT

ION

4 F

IRST

AID

MEA

SUR

ESIN

HAL

ATIO

Nhellip

SKIN

CO

NTA

CThellip

EYE

CON

TACT

hellipIN

GES

TIO

Nhellip

SECT

ION

5 F

IRE

FIG

HTI

NG

MEA

SUR

ES

Wha

t sho

uld

you

do if

exp

osed

Doe

s it

caus

e ca

ncer

85

SECT

ION

6 A

CCID

ENTA

L R

ELEA

SE M

EASU

RES

AIR

RELE

ASE

Redu

ce v

apor

s w

ith w

ater

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88

National Aeronautics and Space Administration

George C Marshall Space Flight CenterHuntsville AL 35812wwwnasagovmarshall

wwwnasagov

NP-2015-07-59-MSFCG-103255b

  • 2016 NASA Student Launch SL Colleges Universities Non-Academic Handbook
    • Table of Contents
      • Timeline for NASA University Student Launch Initiative
      • Acronym Dictionary
        • ProposalStatementof Work for CollegesUniversitiesNon-AcademicTeams
          • Design Development and Launch of a Reusable Rocket and Autonomous Ground Support Equipment Statement of Work (SOW)
            • Vehicle Requirements
            • Recovery System Requirements
            • Competition and Payload Requirements
            • Safety Requirements
            • General Requirements
              • Proposal Requirements
                • VehiclePayload Criteria
                  • Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria
                  • Critical Design Review (CDR)Vehicle and Payload Experiment Criteria
                  • Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria
                  • Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria
                  • Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria
                  • Educational Engagement Form
                    • Safety
                      • High Power Rocket Safety Code
                      • Minimum Distance Table
                        • Related Documents
                          • USLI Competition Awards
                          • NASA Project Life Cycle
                            • Topics
                            • PurposeObjectives of the NASA Project Life Cycle
                            • Typical NASA Project Life Cycle
                            • Student Launch Projects Life Cycle
                            • Preliminary Design Review
                            • Critical Design Review
                            • Flight Readiness Review
                              • Hazard Analysis
                                • What is a Hazard
                                • Hazard Description
                                • Example Hazard Description
                                • Risk
                                • Risk Matrix Example
                                • Risk Continued
                                • MitigationsControls
                                • Verification
                                • Example Hazard Analysis
                                  • Understanding MSDSrsquos
                                    • What is an MSDS
                                    • What is an MSDS
                                    • Required data for MSDSrsquos
                                    • Required data for MSDSrsquos (Cont)
                                    • Important Agencies
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • NFPA Diamond
                                    • Important Agencies (Cont)
                                    • Important Agencies (Cont)
                                    • Exposure Limits
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Exposure Limits (Cont)
                                    • Chemical and Physical Properties
                                    • Chemical and Physical Properties (Cont)
                                    • Things you should learn from MSDSrsquos
                                    • Take your time
                                    • Slide Number 20
                                    • Slide Number 21
                                    • Slide Number 22
                                    • Slide Number 23
                                    • Slide Number 24
                                    • Slide Number 25
                                    • Slide Number 26