Madison West High SchoolMadison West High SchoolGreen TeamGreen Team

The Effect of Gravitational The Effect of Gravitational Forces on Arabidopsis Forces on Arabidopsis Thaliana DevelopmentThaliana Development

Critical Design ReviewCritical Design Review

Vehicle Mission Success CriteriaVehicle Mission Success Criteria

1. Ignition of first stage2. Stable boost of first stage3. Stage separation4. Ignition of second stage5. Stable boost of second stage6. Recovery system deployment of first stage

(simultaneously occurring with the stable boost of the second stage): parachute must deploy

7. Second stage reaching altitude of one mile8. Recovery system deployment of second stage

Figure 2A: A Rocket design drawing with CP and CG marked.

Figure 2B: A 3D model of the rocket. The red section indicates where the accelerometer will be located. The payload will be placed in the green sections. The recovery systems for both stages are above the payload in each stage to allow each stage to decent in the “upside up” manner.

Vehicle DesignVehicle Design

Overall Vehicle SchemeOverall Vehicle Scheme2nd stage• High g’s (40+)• Supersonic• Dual deployment• Drogue in apogee• Main at 500ft

1st stage• Low g’s (5-10)• Single deployment• Timed staging• Timed deployment

Drogue ParachuteAlt/Acc/Timer/RDASBiological PayloadMain/PYL ParachuteMotorsTracking beacon (AM)

LEGEND

Figure 5. Flight Sequence

Flight SequenceFlight Sequence

1. Stage Coupling Tube1. Stage Coupling Tube2. Motor Mount for second stage2. Motor Mount for second stage3. Centering Rings3. Centering Rings

Stage CouplingStage Coupling

4. Timer for stages separation4. Timer for stages separation5. Igniter for 2n stage motor5. Igniter for 2n stage motor6. Timer for 26. Timer for 2ndnd stage ignitionstage ignition7. Igniter for 27. Igniter for 2ndnd stagestage

Transition Legend

Electronic BayElectronic Bay

Second Stage Electronics Bay Legend1. Ejection Charge for drogue parachute2. RDAS and Accelerometer3. Primary Altimeter4. Back-up Altimeter5. Ejection Charge for main parachute

V1: Integrity/robustness testV2: Low altitude test flightV3: Parachute drop testV4: Tension testV5: Prototype flightV6: Functionality testV7: Altimeter ground testV8: Radio signal testV9: Electronic deployment testV10: Ejection testV11: Computer Simulation

Verification Plan and StatusVerification Plan and Status

C1: BodyC2: AltimeterC3: AccelerometerC4: ParachutesC5: FinsC6: PayloadsC7: Timers (for separation and staging)C8: Ejection chargesC9: Radio beaconC10: Launch systemC11: Motor mountC12: Audio tracking (screamers)

Verification Plan and StatusVerification Plan and Status

FPC12

PPC11

PC10

FFPC9

PPC8

PFPPC7

PC6

PPPPC5

PPPPC4

PFPPC3

FFPPC2

PPC1

V11V10V9V8V7V6V5V4V3V2V1

Verification Matrix LegendP: Planned testsF: Finished tests

Verification MatrixVerification Matrix

Design at System LevelDesign at System LevelRequired Subsystems:Required Subsystems:

First Stage: First Stage: Propulsion System, Structural Propulsion System, Structural System, Payload Bay System, Deployment System, Payload Bay System, Deployment System, Recovery System, Tracking SystemSystem, Recovery System, Tracking System

Second Stage: Second Stage: Propulsion System, Structural Propulsion System, Structural System, Payload Bay System, Deployment System, Payload Bay System, Deployment System, Recovery System, Tracking SystemSystem, Recovery System, Tracking System

Other: Other: Launch System, Recovery SystemLaunch System, Recovery System

First StageFirst StageFirst Stage:First Stage:

Propulsion System: Propulsion System: The propulsion system The propulsion system will consist of a J class hybrid motor unit will consist of a J class hybrid motor unit ((SkyRipperSkyRipper system), fueled by nitrous oxide system), fueled by nitrous oxide and polyvinyl chloride. This will be inserted and polyvinyl chloride. This will be inserted into the motor mount, which will be centered into the motor mount, which will be centered inside the rocket body by three aircraft inside the rocket body by three aircraft plywood rings. The motor will be held in by plywood rings. The motor will be held in by the active retention system (dual Lthe active retention system (dual L--clamps).clamps).

First StageFirst StageFirst Stage First Stage con’tcon’t

Structural System: Structural System: The structural system will consist of The structural system will consist of a 6a 6--inch tube covered with Fiberglass and three fins inch tube covered with Fiberglass and three fins made of G10 Fiberglass.made of G10 Fiberglass.

Payload Bay System: Payload Bay System: The payload bay system will be The payload bay system will be a a phenolicphenolic tube that houses Petri dishes, and will be tube that houses Petri dishes, and will be sealed with plywood caps on both ends. This whole unit sealed with plywood caps on both ends. This whole unit is then placed in the rocket.is then placed in the rocket.

Deployment System: Deployment System: The deployment system will The deployment system will consist of two timers for stage separation and parachute consist of two timers for stage separation and parachute deployment. The timers will ignite electronic matches to deployment. The timers will ignite electronic matches to set off a deployment charge.set off a deployment charge.

Second Stage:

• Propulsion System: The propulsion system will consist of a solid-fuel J class motor. This will be inserted into the motor mount, which will be centered inside the rocket bodyby two aircraft plywood rings.

• Structural System: The structural system will consist of a 4-inch tube covered with Kevlar and three fins made of G10 Fiberglass.

• Payload Bay System: same as in the first stage

Second StageSecond Stage

Deployment SystemDeployment SystemDeployment System: The deployment system for the second stage will be two dual event altimeters. They will both fire the same charge at the apogee to deploy drogue parachute, and then again they both will fire another charge to deploy the parachute at 500 feet. We are using two altimeters so we have some redundancy (if one fails, the other one still fires the necessary charges).

Tracking and Recovery SystemsTracking and Recovery Systems

Tracking System: The tracking system will consist of an AM radio beacon and two 140dB screamers.

Recovery System: We will use a single deployment system for the first stage and a dual deployment system for the second stage. For sizes of the parachutes, see the table on the next slide.

Other:

Launch System: This system consists of the ground support equipment for the SkyRipper Hybrid Motor System and a launch tower.

5.81570Second Stage Main+Drouge

5.85015Second Stage Drogue

11.0 1596First Stage Main

Weight (lbs)

Descent Rate (fps)

Parachute Size (in)

Parachute SizeParachute SizeRecovery System: Recovery System: We will use a single deployment system for We will use a single deployment system for the first stage and a dual deployment system for the second the first stage and a dual deployment system for the second stage. The sizes for the parachutes and the drop rates during stage. The sizes for the parachutes and the drop rates during vehicle recovery will be as follows:vehicle recovery will be as follows:

We use the igniters and motors properly so they do

ignite.

Nothing happens. First Stage Failure—rocket doesn’t ignite

Sturdy materials (Kevlar, fiberglass, epoxy, etc.) that can sustain the stresses of

the flight will be used.

Rocket disintegrates. Faulty Design—structural failure

We are doing computer simulations, low altitude

flights, and prototype flights to make sure that the rocket

is stable

Unsuccessful flight. Faulty Design—unstable rocket

We will do extensive testing of staging mechanisms

during prototype and test flights

Second half of experiment is not carried out.

Rocket doesn’t stageMitigation Result Problem

Launch Risk PlotLaunch Risk Plot

Launch rod will be leveled, lubricated, and secured to a

stable surface.

Rocket leaves launch pad at an undesired angle.

Launch failure—launch rod malfunction

Motors are properly stored and used.

Rocket explodes. (Severe damage to the rocket and

motor casing.)

Staging Failure—catastrophic motor malfunction

Parachute will be properly prepared and installed before

the launch.

Ballistic fall of rocket and/or payload.

Recovery Failure—parachutes fail to deploy or

become tangledRocket will be properly

packaged for transportation and inspected carefully

before the launch.

Possible aberrations in launch, flight, or recovery

Transportation—rocket is damaged during

transportation

The stages will be attached loosely so that they can

separate easily.

First Stage is severely damaged. The plants are

destroyed due to exposure to heat.

Stage Separation Failure-Second stage does not separate from first stage

Launch Risk Plot Launch Risk Plot con’tcon’t

Launch Risk Plot Launch Risk Plot con’tcon’t

Test RDAS during test flights and prior to launching to

ensure that it is functioning properly before being inserted

in the rocket. Insert fresh batteries prior to launch.

We would have no acceleration data.

RDAS Failure

Parachute shock cords will be carefully folded and inserted

to prevent entanglement.

Unsafe landing of rocket.Parachute is Tangled

A tracking system will be used to locate the rocket. Radio

beacon and screamers provide help in finding the

rocket.

Rocket is lost. Mission failure.Rocket is Carried off by Strong Wind

Rigorous tests of the timers’accuracy will be performed

during test flights.

Stages do not separate and/or parachutes/ drogue do not

deploy.

Timers Do Not Initiate Reaction at the Proper Time

1.Successful two stage flight

2. Altitude of one mile reached as accurately as possible

3. Successful recovery of both stages

4. Payload not damaged

5. Successful collection of acceleration profile

Mission Performance CriteriaMission Performance Criteria

2.40/2.320.0836465215J270/J800201.23/1.164.5664295248J270/J800152.23/4.886.5549225168J270/J800102.22/5.268.0491195271J270/J80052.21/5.499.0458185243J270/J8000

Stability Margins (2nd Stage/ 1st Stage)

Ballast in second stage (lbs)

Max Velocity (mph)

Max Accel(gee's)

Apogee (ft)MotorsWind Speed (mph)

Simulation ResultsSimulation Results

Figure 1: Simulated acceleration profile for both stages

Flight Profile SimulationsFlight Profile Simulations

Figure 4: Altitude vs. Time (wind speed = 10 mph, ballast weight = 6.5 lbs.,first stage motor: J270, second stage motor: J800)

Flight Profile Simulations Flight Profile Simulations con’tcon’t

Payload IntegrationPayload Integration

Payload consists from stacks of Petri Payload consists from stacks of Petri dishes housed in a coupler tube. The dishes housed in a coupler tube. The payload fits snuggly in the second stag 4” payload fits snuggly in the second stag 4” body. The first stage body is larger and 4” body. The first stage body is larger and 4” payload housing will be centered inside payload housing will be centered inside the tube by three centering rings. the tube by three centering rings. The electronics will be housed in standard The electronics will be housed in standard ee--bays built out of a coupler tube and bays built out of a coupler tube and plywood caps.plywood caps.

1.Check structural integrity of rocket2.Attach parachutes to shock cords and attach shock

cords to rocket sub assemblies3.Assemble and insert the first payload into the first

stage assembly4. Insert parachutes into the first stage assembly5.Assemble and insert the second payload into the

second stage assembly6. Insert parachutes into the second stage assembly7.Assemble the rocket8.Assemble the re-loadable motor9. Insert and secure motor into the motor mount

Final Assembly ProceduresFinal Assembly Procedures

First Stage Final Assembly First Stage Final Assembly ProceduresProcedures

First Stage Preparation and RecoveryFirst Stage Preparation and RecoveryLoad the payload capsule gently into the first stage body tube.Load the payload capsule gently into the first stage body tube.Verify that the first stage electronics (one timer) are functionVerify that the first stage electronics (one timer) are functional al and have the correct settings and disarm electronics.and have the correct settings and disarm electronics.An adult will prepare an ejection charge for the electronic An adult will prepare an ejection charge for the electronic deployment of the first stage parachute.deployment of the first stage parachute.Attach the ejection charge to electronics bay (eAttach the ejection charge to electronics bay (e--bay) terminal.bay) terminal.Insert first stage eInsert first stage e--bay on top of payload with the ebay on top of payload with the e--bay terminal bay terminal and ejection charge on top.and ejection charge on top.Place the rest of the first stage body tube on the ePlace the rest of the first stage body tube on the e--bay and bay and secure the esecure the e--bay to the first stage body with screws.bay to the first stage body with screws.Attach the first stage parachuteAttach the first stage parachute’’s shock cord to the hook on the s shock cord to the hook on the ee--bay, insert the shock cord in the body tube in the proper bay, insert the shock cord in the body tube in the proper manner and place folded first stage parachute on top.manner and place folded first stage parachute on top.

Second Stage Final Assembly Second Stage Final Assembly ProceduresProcedures

Second Stage Preparation and RecoverySecond Stage Preparation and RecoveryLoad the payload capsule into the upper stage body tube.Load the payload capsule into the upper stage body tube.An adult will prepare an ejection charge with two electronic matAn adult will prepare an ejection charge with two electronic matches and put ches and put them in the rocket with their wire hanging out of the tube.them in the rocket with their wire hanging out of the tube.Attach shock cord to the top of the payload capsule, insert the Attach shock cord to the top of the payload capsule, insert the cord in the cord in the proper manner, and place the second stage main parachute on top proper manner, and place the second stage main parachute on top of the of the shock cord and ejection charge.shock cord and ejection charge.Verify the electronics (RDAS, altimeters, and timer) are functioVerify the electronics (RDAS, altimeters, and timer) are functional and have nal and have the correct settings and disarm electronics.the correct settings and disarm electronics.An adult will prepare another ejection charge with two electroniAn adult will prepare another ejection charge with two electronic matches.c matches.Attach one wire from each ejection charge to each altimeter.Attach one wire from each ejection charge to each altimeter.Place the ePlace the e--bay onto the second stage body tube with the second ejection bay onto the second stage body tube with the second ejection charge and the terminal on top.charge and the terminal on top.Attach the drogue parachute shock cord to the hook on the eAttach the drogue parachute shock cord to the hook on the e--bay. bay. Put in the parachute in the proper manner.Put in the parachute in the proper manner.Put on the nosecone.Put on the nosecone.

Propulsion SystemsPropulsion Systems

Motor PreparationMotor Preparation

The motors will be prepared by Scott Goebel, The motors will be prepared by Scott Goebel, our NAR mentor.our NAR mentor.

The motors are solid fuel J for the upper stage The motors are solid fuel J for the upper stage and a hybrid J for the lower stage, they will be and a hybrid J for the lower stage, they will be assembled and prepared in their respective assembled and prepared in their respective motor mounts by Mr. Goebel.motor mounts by Mr. Goebel.

Throughout these motor preparation procedures, Throughout these motor preparation procedures, all the electronics in the rocket will be disarmed.all the electronics in the rocket will be disarmed.

Setup on LauncherSetup on Launcher

We will use a rail system, which will We will use a rail system, which will be tilted to allow for ease of insertion.be tilted to allow for ease of insertion.

We will slide the rail buttons into the We will slide the rail buttons into the rail, and tilt it back up.rail, and tilt it back up.

1.Place assembled rocket on launch rail2. Insert igniter into the assembled motor3.Active payload electronics4.Activate altimeter to arm the ejection charges5.Activate separation/staging electronics6.Connect igniter to the launch system7.Check continuity8.Arm ejection charges9.Check sky for aircraft10.Arm ignition system11.Countdown12.Launch

PrePre--Launch ProceduresLaunch Procedures

PostPost--Flight InspectionFlight Inspection

Post Flight InspectionPost Flight Inspection

Make sure all charges have fired during flight.Make sure all charges have fired during flight.Deactivate all electronics and sonic beacons.Deactivate all electronics and sonic beacons.Remove payload first and check for damage.Remove payload first and check for damage.Download data from the RDAS and altimeters.Download data from the RDAS and altimeters.Let the motor casings cool down and then Let the motor casings cool down and then remove from rocket, checking for damage.remove from rocket, checking for damage.

Disarming and ReDisarming and Re--arming arming ProcedureProcedure

1. Remove ignition interlock to prevent accidental ignition

2. Wait designated time by HPR safety code (1 minute)

3. Disarm electronics and remove rocket from pad

4. Reinstall igniter

5. Place rocket back on pad, re-arm electronics

6. Test continuity

SafetySafety

NAR safety codes will be observedNAR safety codes will be observedA safety briefing will be conducted prior each A safety briefing will be conducted prior each launchlaunchProcedure and safety code knowledge of all Procedure and safety code knowledge of all members will be test on regular basismembers will be test on regular basisAll devices will be used in the accordance with All devices will be used in the accordance with manufacturers instructions and the operational manufacturers instructions and the operational manuals for all devices will be always on handmanuals for all devices will be always on handAll electronics will have arming switchesAll electronics will have arming switchesOnly a certified mentor will handle the motors Only a certified mentor will handle the motors and ejection chargesand ejection chargesSafety equipment will be used as requiredSafety equipment will be used as required

February 200611th Stress test of the second stage 16th Payload integration starts

Payload capsules evaluated18th Two-stage flight, no payload, ¼ mile altitude25th Second Stage flight with planted payload capsules28th Test flights evaluated, design changes made

March 20067th Rocket design changes and payload capsule improvements finished

Major Milestone ScheduleMajor Milestone Schedule

Major Milestone Schedule Major Milestone Schedule con’tcon’tApril 20068th Two stage flight with payload, ½ mile altitude9th ½ mile altitude test flight evaluated, improvements to design and to payload suggested14th Design improvements and changes finished22nd Two-stage flight with payload, one mile altitude 23rd Last repairs and improvements start28th Rocket ready for final SLI Launch

May 20063rd–7th SLI Final Meet/Launch in Huntsville

PAYLOAD OBJECTIVEPAYLOAD OBJECTIVE

The goal of the payload is The goal of the payload is to observe how to observe how Arabidopsis thaliana Arabidopsis thaliana young plants or young plants or seedlings react to the seedlings react to the strong, sudden forces strong, sudden forces associated with the associated with the acceleration of a rocket acceleration of a rocket launch.launch.

PAYLOAD OUTLINEPAYLOAD OUTLINE33--4 days post4 days post--germinationgerminationPlants will be subjected to two brief jolts of Plants will be subjected to two brief jolts of acceleration during launchacceleration during launchShort and longShort and long--term developmental effects of term developmental effects of acceleration will be testedacceleration will be tested

EXPERIMENTAL RATIONALEEXPERIMENTAL RATIONALEMeasures potential sources of error in Measures potential sources of error in launching biological payloads for space launching biological payloads for space missionsmissionsConventional acceleratoryConventional acceleratory--forces studies forces studies are longerare longer--term, lowerterm, lower--intensity while ours intensity while ours study concentrates on short, high intensity study concentrates on short, high intensity force applicationsforce applicationsGeneticallyGenetically--designed and designed and --altered plants altered plants are increasingly important in plant are increasingly important in plant sciencessciences

ROCKET DATA ACQUISITION ROCKET DATA ACQUISITION SYSTEMSYSTEM

RDAS unit in will record acceleration profileRDAS unit in will record acceleration profileResults will be used as estimation of Results will be used as estimation of acceleratory forces applied to plantsacceleratory forces applied to plantsLocated in sustainer’s electronics bayLocated in sustainer’s electronics bayMeasures within 0.1g; however, dampening Measures within 0.1g; however, dampening effects from agar may somewhat reduce effects from agar may somewhat reduce accuracyaccuracy

ARABIDOPSIS ARABIDOPSIS STRAINSSTRAINS

Mutant strain will be Mutant strain will be agravitropicagravitropic, , containing a genetic alteration reducing containing a genetic alteration reducing sensitivity to gravity & acceleratory forcessensitivity to gravity & acceleratory forcesOther strain will be normal (“wild type”) Other strain will be normal (“wild type”) plantsplantsBoth strains used will contain a genetic Both strains used will contain a genetic marker that facilitates root growth analysis marker that facilitates root growth analysis (gene marker DR5(gene marker DR5--GUS)GUS)

PAYLOAD STRUCTUREPAYLOAD STRUCTURE4” Petri dishes with MS Media nutrient agar4” Petri dishes with MS Media nutrient agar

2.5 % solution, 10mL per dish2.5 % solution, 10mL per dish30 seeds will be placed on each dish 30 seeds will be placed on each dish –– one one strain per dishstrain per dishMaximizing agar uniformity and distances Maximizing agar uniformity and distances between seedsbetween seeds

PAYLOAD BAY STRUCTUREPAYLOAD BAY STRUCTUREBulkheadPadding foamSingle Petri dish

EXPLODED VIEW

ASSEMBLED VIEW

Anchoring Screw

OVERALL PAYLOAD STRUCTUREOVERALL PAYLOAD STRUCTURE

Sustainer Payload Section

Booster Payload Section

Control Plants

(non-flying)

PLANT STRAINS

Unaltered Plants

Agravitropic Plants

Petri dishes containing both strains of Arabidopsis will be placed in three locations (1st stage (< 7g), 2nd

stage (~40g), ground).

PAYLOAD LOCATION LEGEND

PAYLOAD SUCCESS PAYLOAD SUCCESS CRITERIA CHECKLISTCRITERIA CHECKLIST

30 seeds per section, per strain survive30 seeds per section, per strain survive

RDAS records accurate dataRDAS records accurate data

Each stage reaches distinct accelerationEach stage reaches distinct acceleration

Petri dishes remain sterile, undamagedPetri dishes remain sterile, undamaged

Seedlings survive preSeedlings survive pre-- and postand post--flightflight

Integration modules remain intactIntegration modules remain intact

Microscopic root analysis will be Microscopic root analysis will be employed to obtain a detailed employed to obtain a detailed picture of root structure and the picture of root structure and the presence of traumatic damage presence of traumatic damage to cells.to cells.

We will use standard light We will use standard light microscopes as well as highmicroscopes as well as high--resolution dissecting scopes resolution dissecting scopes (on loan from the University of (on loan from the University of Wisconsin).Wisconsin).

RESULTS ANALYSIS TECHNIQUE 1/3RESULTS ANALYSIS TECHNIQUE 1/3MICROSCOPIC ANALYSISMICROSCOPIC ANALYSIS

GENE MARKER ANALYSISGENE MARKER ANALYSISWhen a stain is applied to the plants, cells containing the genetic marker DR5-GUS are identified. These cells are root growth promoters called auxins, allowing us to visually track root growth under a dissecting scope.

Blue stain applied

RESULTS ANALYSIS TECHNIQUE 2/3RESULTS ANALYSIS TECHNIQUE 2/3

LONGLONG--TERM GROWTH ANALYSISTERM GROWTH ANALYSISPostPost--launch, approximately 1/3 of launch, approximately 1/3 of

the seeds from each strain and the seeds from each strain and section will be grown to maturity. section will be grown to maturity. After they reach the maximum After they reach the maximum development possible within the development possible within the Petri dishes, they will be Petri dishes, they will be transferred to nutrienttransferred to nutrient--enriched enriched soil.soil.

Frequent observations, comparing Frequent observations, comparing each type of plant to the control, each type of plant to the control, will be made in order to track any will be made in order to track any alterations caused by the launch.alterations caused by the launch.

RESULTS ANALYSIS TECHNIQUE 3/3RESULTS ANALYSIS TECHNIQUE 3/3

PREPRE--LAUNCH GROWTH LAUNCH GROWTH PROCEDURESPROCEDURES

One week prior to launch, 8 One week prior to launch, 8 dishes each of wild type and dishes each of wild type and agravitropicagravitropic seeds will be seeds will be plated with 15 seedsplated with 15 seedsAfter growing under lights until After growing under lights until the launch date, the 12 the launch date, the 12 healthiest dishes will be healthiest dishes will be installed in the integration installed in the integration modulesmodulesPostPost--launch, all dishes will be launch, all dishes will be transferred back to growing transferred back to growing conditionsconditions

Schematic of booster integration module