STUDENT LAUNCH INITIATIVE 2011 – 2012 AIAA OC Rocketeers FRR Presentation April 9, 2012

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STUDENT LAUNCH INITIATIVESTUDENT LAUNCH INITIATIVE2011 – 20122011 – 2012

AIAA OC RocketeersAIAA OC RocketeersFRR PresentationFRR Presentation

April 9, 2012April 9, 2012

Student Launch Initiative

AIAA OC Rocketeers

AgendaAgenda Introduction of team members (representing 4 high schools in Introduction of team members (representing 4 high schools in

Orange County California)Orange County California) Full Scale DesignFull Scale Design

• Vehicle – Design, Construction, Flight testsVehicle – Design, Construction, Flight tests• UAV Payload – Description, Safety, and TestingUAV Payload – Description, Safety, and Testing• UAV Flight TestsUAV Flight Tests• Wingless UAVWingless UAV• Recovery System and EventsRecovery System and Events• GPSGPS• IntegrationIntegration

Risks and SafetyRisks and Safety Educational OutreachEducational Outreach Budget and TimelineBudget and Timeline

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Modifications Since Original PostingModifications Since Original Posting Updated SlidesUpdated Slides

• Full Scale DesignFull Scale Design• Payload slidesPayload slides• Recovery Recovery

Added slidesAdded slides• Full Scale Test FlightFull Scale Test Flight• UAV Test flightUAV Test flight• Wingless UAV Wingless UAV • Black Powder Charge testsBlack Powder Charge tests• Lessons LearnedLessons Learned

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FullFullScaleScale

DesignDesign

Vehicle – Full ScaleVehicle – Full Scale

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Parameter Details

Length/Diameter 130.1 inches / 5 inches

Material .075” thick filament wound Carbon Fiber from Performance Rocketry

Shock Cord 1” Tubular Nylon

Center of Pressure/Center of Gravity 111.5”/93.3”behind nose tip

Stability Margin 3.64

Launch System / Exit Velocity 1” 8ft Rail / 80.4 ft/s

Vehicle – Full Scale cont’dVehicle – Full Scale cont’d

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Parameter Details

Liftoff Weight 35.6 lbs

Descent Weight 32.6 lbs

Preferred Motor Aerotech K1050

Thrust to weight ratio 6.63 (1050 Newtons average thrust = 236 N / 35.6 lb vehicle)

Maximum ascent velocity 537 ft/s

Maximum acceleration 313 ft/s/s

Peak Altitude 3906 ft

Drogue – Descent rate 66.38 ft/s

Lower section under Main – Descent rate (Kinetic energy at ground level)

21.21 ft/s (61.79 ftlb-force)

Upper section under its own chute – descent rate (Kinetic energy at ground level)


UAV on its own parachute – descent rate (Kinetic energy at ground level if UAV is not released)


Vehicle – Forward SectionVehicle – Forward Section

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Parameter Details

Nose Cone Carbon Fiber 24” long

Body Tube .075” thick Carbon fiber 5” diameter x 56” long

Bulkhead ½” plywood with fiberglass on both faces with “U” bolt for shock cord attachment

Shock Cord 1” Tubular Nylon x 20 ft + 4 ft (Piston)

Sabot Carbon Fiber coupler, split lengthwise, hinged

Forward Cavity 10” x 5” diameter for ejection charge, shock cord, GPS, and forward section parachute (56” – 5” for avionics bay – 5” for nose cone – 31” for sabot – 5” for piston)

Ejection Charge 1.6 grams (250 lbs)

Vehicle – Avionics BayVehicle – Avionics Bay

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Parameter Details

Bay Material Carbon Fiber tubing 12” long – coupler for 5” body tube


Bulkhead ½” plywood with fiberglass on outrer faces with closed eye bolt for shock cord attachment

Sled 1/8” plywood with ¼” threaded rods the entire length

Electronics HCX and Raven flight computers, Batteries

Terminal Blocks (for ejection chg)

Aft: Drogue primary and backup, Main primary and backupForward: UAV deploy primary and backup

Vehicle – Rear SectionVehicle – Rear Section

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Parameter Details


Centering Rings 2ply x 3/32” = 3/16” fiberglass with “U” bolt for shock cord

Shock Cord 1” Tubular Nylon x 15 ft + 15 ft + 6 ft (across Tender Descender)

Rear Cavity 16” x 5” diameter for ejection charge, shock cord, GPS, and forward section parachute (48 – 5” for avionics bay overlap - 27” for motor)

Ejection Charge 3.9 grams (250lbs)

Tender Descender

.2 grams (per the data sheet)

Aerotech K1050Aerotech K1050(Alternate: Cesaroni K1440) (Alternate: Cesaroni K1440)

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Designation K-1050W-SU Total Weight 2128 grams

Manufacturer Aerotech Propellant Weight

1362 grams

Motor Type Single Use Average Thrust 1050.0 N

Diameter 54.0 mm Maximum Thrust 2164.0 N

Length 67.6 cm Total Impulse 2530.0 Ns

Propellant White Lightning

Burn Time 2.3 s

Cert Organization

TRA Isp 189 s

Launch SimulationsLaunch Simulations

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• Simulations were run using Rocksim• Over 100 simulations were run to fine tune vehicle• Dimensions, weights, and launch conditions were varied• Once vehicle was designed varied engines to reach the altitude closest to 1 mile• Verified top speed was still subsonic• Verified range with varied winds

Vehicle ConstructionVehicle Construction

• Bulkheads and centering rings are laminated 3/16” thick fiberglass Bulkheads and centering rings are laminated 3/16” thick fiberglass with 1/8” thick honeycomb or 9 layer plywood betweenwith 1/8” thick honeycomb or 9 layer plywood between

• Fins are 0.188” thick fiberglassFins are 0.188” thick fiberglass• Proline 4500 high temperature epoxy is used on the motor tubeProline 4500 high temperature epoxy is used on the motor tube• West systems epoxy is used everywhere else on the bodyWest systems epoxy is used everywhere else on the body• Attachment points are all “U” boltsAttachment points are all “U” bolts 1212


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The vehicle is made of composite materials

• Body tube is 5” diameter .075” thick filament wound carbon fiber• The nose cone is the same material• Sabot is thinner couple but of the same material

Bulkheads and ringsBulkheads and rings

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To keep down weight in this carbon fiber vehicle, all bulkheads and centering rings use composite construction with fiberglass sandwiching light-weight honeycomb material or, where more strength is required, 9 layer ½” thick plywood

Body TubesBody Tubes

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The carbon fiber body tubes cut relatively easily using a hacksaw

Lengthwise cuts for the sabot and fin slots were made using a Dremel tool

The carbon fiber was under a great deal of compression and wanted to close in on itself during the cutting

Motor MountMotor Mount

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The motor mount is made of 2 12” long 54mm fiberglass motor tubes

They are joined together with the ½” thick composite fiberglass – plywood centering ring reinforced with fiberglass tape

The other two rings are composite fiberglass and honeycomb

Other DetailsOther Details

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The sabot end caps are ½” thick 9 ply plywood with fiberglass on the outer end

Heavy “U” bolts and hinge are used

The avionics by is stepped plywood to promote a good seal capped with fiberglass – the inside is sprayed with an RF shield

Fin attachmentFin attachment

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Fins are carefully marked using the fin jig

Fins are epoxied in place using high temperature and West Systems adhesive

Alignment is held when epoxy cures in the fin jig

The end is left open to reinforce the joints

Finally, fiberglass tape is applied

Full Scale 1Full Scale 1stst Test Flight Plaster City Test Flight Plaster City

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• Full Scale Model was flown at Plaster City

• Used dual redundant dual deploy for a recovery system

• vehicle was stable with an extremely straight flight

• Sabot deployed wingless UAV properly

• Main parachute did not deploy due to a missing quick-link

Full Scale 2Full Scale 2ndnd Test Flight Plaster Test Flight Plaster City City

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• Full Scale Model was flown at Plaster City

• Used dual redundant dual deploy for a recovery system

• vehicle was stable once again with an extremely straight flight

• The Tender descender cap brokeand the main parachute did notdeploy

UAV Payload SystemUAV Payload System

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The UAV Payload has been simplified since the original proposal due to

• Safety concerns (recovery in the event of partial system failure)• Space and weight limitations of the UAV• Time constraints

The UAV System consists of• 2.4 GHz RC Control via Spektrum DX-8• 434.92 MHz GPS real time downlink• 1.2 GHz Video downlink• Video data converted to USB for interface similar to web cam

Note: Rocket also uses two separate GPS transmitters for tracking

UAV Mechanical ComponentsUAV Mechanical Components

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• Mechanically, the UAV is composed of two main parts

• Bendable wing developed at University of Florida• Fuselage, vertical and horizontal stabilizer (modified to fit) from the Electrifly RC Airplane

• Wing • Wingspan 30 inches• Weight 12 grams• Material Carbon Fiber

• Fuselage• Length 30 inches• Weight 140g• Material fiberglass

• Parachute release mechanism is electrically controlled servo activated by one channel of the AR-8000 RC receiver• Vehicle with electronics is 1.4 lb

Bendable Wing Bendable Wing FabricationFabrication

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• Wing design was developed at University of Florida (UF) for use in UAVs deployed from a tube• Northrop Grumman used their CNC machine to make three molds mold (18”, 24”, and 30”) from our file and tooling board • Carbon fiber cloth is 6 oz 3K Twill Weave pre-preg• Cloth is laid at 45 degree angle to direction of motion of the wing through the air• Northrop Grumman formed our wing from our mold using their non-flight autoclave • Cloth is laid over the mold and placed in a vacuum bag (mold and vacuum bag are protected with release film• The pressure is then lowered as close to 30” of mecury as possible• The vacuum bag and contents are baked at 260 – 350 degrees for about 6 hours

Bendable Wing Bendable Wing FabricationFabrication

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• After the wing is removed from the mold it must be trimmed to the correct size

• Carbon Fiber is relatively easy to trim with a stout pair of scissors

• The rough edges can then be sanded smooth with a bench sander

Bendable Wing Bendable Wing CharacteristicsCharacteristics

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• The carbon fiber wing is formed similar to a tape measure

• It will bend in one direction easily – but not the other direction

• The wing can wrap around the fuselage

• The entire UAV with wrapped wings can then fit inside the sabot

UAV DesignUAV Design

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• Originally an Electrifly Rifle RC Plane• Selected for its size and fiberglass body • Wingspan: 31 inches• Wing Area: 112 square inches• Weight: 18 oz• Wing loading: 22 – 23 oz/square ft• Length: 24.5 inches• Control Surfaces: Ailerons and Elevator

• The final UAV• Wingspan: 28”• Wing Area: Approx 190 square inches• Weight : 22 oz• Wing loading: 16 – 17 oz/square ft• Length: 25.5 inches• Control Surfaces: Rudder and Elevator

UAV Elevated WingUAV Elevated Wing

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• Wing is elevated on a tower from the original Rifle design to

• Give the wing room to maximize the use of the inside diameter of the sabot

• Provide more space for added electronics and batteries

• Put most of the weight under the wing to minimally affect the center of gravity

UAV Video TowerUAV Video Tower

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• This tower provides space for all video equipment and power source in one module

• Video Camera (640 x 480 CMOS NTSC)• Battery (11.1 V 550 mAh)• Video Transmitter (Lawmate 1Watt)• 1.2GHz low pass filter• 3dB gain antenna

• Power remains off until turned on via a microswitch when UAV is deployed

UAV Tail UAV Tail ModificationsModifications

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• Original tail was “T” with elevators on horizontal stabilizer and no rudder (wing had ailerons)• Now cruciform to use maximum width in sabot for maximum surface area• Added rudder to vertical stabilizer

UAV Range TestingUAV Range Testing

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• Ground station was 1.2GHz receiver• Dronesvision 14 dB gain patch antenna• Happauge video to USB converter• Video was turned ON in UAV and team members walked away from ground station• Same test run with Spektrum transmitter and control surfaces

Range Testing ResultsRange Testing Results

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• Video end of range was non-usable picture• RC end of range was incosistent movement of controlled surfaces

Test Max Distance

Video .55 miles

RC Control – diversity antenna near ESC

.15 miles

RC Control – diversity antenna near tail

.48 miles

UAV Flight Test 1UAV Flight Test 1

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• The team enlisted the help of Mark Slizie, manager of a local Hobby People store

• Mark gave the team guidance on modification of the Rifle

• We went to test fly with the Orange Coast Radio Control Club

• Interference from the Electronic Speed Control into the radio made the control unstable and prevented us from flying


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•We went to go fly with the Orange coast radio control club

•The plane proved to be stable on the first hand launch the plane had power but it was not used

•The plane was powered on the second hand launch but acted strangely

• The first hand launch on landing may have damaged the plane, which caused it to act strangeley

• The plane was damaged on the second hand launch


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• we went to go fly with the Orange coast radio control club

•The repair job was verified

•We tested the plane to make sure everything was properly working

• The motor shaft snapped • We Learned to ALWAYS ground test before

flying

Changes to the UAVChanges to the UAV

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•One of the experienced flyers at Great Park helped us adjust the trim in the servos controlling

•We bought a new prop shaft and placed it in our motor because we could not find another motor that would fix our problem

•Then we mounted the motor on the outside of the UAV so we could have a more secure attachment of the prop to the UAV

•To add stability to the plane, we decided to increase surface area to the tail by adding four plywood pieces in the shape of a diamond to the outside of our cruciform tail

UAV Test Flight 4UAV Test Flight 4

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•Mark Silzle came out to throw our plane for us

•Mark threw the plane 2 times to determine that it was stable enough to fly

•When we found that it was, on the third throw we attempted a powered flight

•In this short flight, controlled by one of our payload members and lasting less than a minute, the UAV was stable when flying straight and turned

•The turn, however, was not easy to control as the UAV tended to want to roll

•We determined that the UAV is flyable, but that turning is a weak point in its design because of the lack of ailerons on the bendable wing

UAV ElectronicsUAV Electronics

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• Main UAV control is via Radio Control (Spektrum DX-8 transmitter and AR-8000 receiver) on 2.4GHz• GPS tracking is done through a Big Red Bee Beeline GPS transmitting on 434.92 MHz• Video is from a CCD camera and relayed to the ground real time via a 1 watt Lawmate 1.2GHz transmitter

UAV Electronics SystemUAV Electronics System

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UAV – Ground StationUAV – Ground Station

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UAV Ground Station• Allows RC control of UAV• Allows detachment of the parachute from the UAV• Displays real time video from the UAV

UAV SafetyUAV Safety

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1. The UAV will descend on parachute until it can be verified it is flightworthy and not fouled on shock cords or shroud lines

2. The UAV detachment from the parachute is manual allowing a human to make the final decision

3. The UAV will be under RC control at all time4. If RC communications is lost the AR-8000 will circle while

losing altitude until back on the ground.5. If the battery dips below a safe voltage for Lithium

Polymer, the high current drain of the motor is disabled and only the radio and servos remain powered to allow the pilot to return the UAV safely to ground

Wingless UAVWingless UAV

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• Contains Ardu Pilot Mega, and all peripherals along with a camera and Lawmate transmitter

•It transmits full telemetry data and video to a ground station during decent

•Contained in a 4inch diameter body tube that is 12 inches in length

RecoveryRecovery

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• Recovery System consists of:• G-Wiz Partners HCX Flight Computer (4 pyro events)• 1.10” x 5.50” 45 grams • Accelerometer based altitude

• Raven Flight Computer (4 pyro events)•1.80" x 0.8" x 0.55." 27 grams • accelerometer based altitude

• Deployment bag with 96” Main Parachute• Two Tender Descenders in series (primary and backup)

Other Parachutes:• 36” Drogue• 48” Parachute for top body section• 24” Parachute on UAV

• Avionics Bay is coated with MG Chemicals SuperShield Conductive Coating 841 to minimize RF Interference

Recovery InterconnectRecovery Interconnect

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• Flight computers are powered from Duracell 9VDC batteries• Raven CPU and Pyro are on separate batteries• HCX CPU and Pyro are on separate batteries

• Design includes 4 safety switches (CPU power on before pyro)• Raven Flight Computer CPU Power• HCX Flight Computer CPU Power • Raven Flight Compuer Pyro Power• HCX Pyro Power

Black Powder ChargesBlack Powder Charges

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• A total of six separate black powder charges are used• The Drogue uses one black powder charge from the HCX pyro 2 as primary and one from the Raven pyro 1 as the backup to deploy at apogee• The Sabot uses one black powder charge from the HCX pyro 3 as primary and one from the Raven pyro 2 as the backup to deploy at an altitude of 1,000 ft• The Main uses one black powder charge from the HCX pyro 4 as primary and one from the Raven pyro 3 as the backup to deploy at an altitude of 800 ft

Black Powder Charge ResultsBlack Powder Charge Results

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Trail Section Amount (G) Successful?

1 Sustainer 2.25 No

2 Sustainer 2.6 No

3 Sustainer 2.9 No

4 Sustainer 3.25 No

5 Sustainer 3.5 No

6 sustainer 3.9 Yes

Black Powder Charge ResultsBlack Powder Charge Results

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Trail Section Amount (G) Successful?

1 Upper – without 1.4lbs in sabot 1.3 Yes

2 Upper – with 1.4lbs in sabot 1.3 No

3 Upper – with 1.4lbs in sabot 1.5 No

4 Upper– with 1.4lbs in sabot 1.6 Yes

Recovery EventsRecovery Events

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• Redundant Dual Deployment from two different flight computers• Deployment consists of three separate events

• Event #1: Near apogee a black powder charge deploys the drogue parachute

• Rocket is in two sections tethered together

• Lower body tube with motor and fins• Nose cone, upper body tube with UAV, avionics bay

• Exposed and on the 1” Nylon shock cord:

• Drogue fully deployed• Main held in bag by Tender Descenders• One of two GPS (to clear carbon fiber body tube)


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• Event #2: At 950 ft (backup at 850 ft) a second black powder charge in the Tender Descenders deploys the main •Lower body tube with motor and fins still on the main parachute tethered to the avionics bay

• Rocket is in two sections tethered together

• Lower body tube with motor and fins

• Nose cone, upper body tube with UAV, avionics bay

• Exposed and on the 1” Nylon shock cord:

• Drogue fully deployed• Main Fully Deployed• One of two GPS (to clear carbon fiber body tube)


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• Event #3: At 800 ft (backup at 750 feet) a third ejection charge separates the rocket further• There are now three pieces descending

• Lower body tube with motor and fins still on Main tethered to the avionics bay only• Upper body tube tethered to the nose cone and the opened sabot is all under another deployed parachute• Second GPS is now exposed on the 1” nylon shock cord• UAV has deployed from the sabot and is under its own parachute

UAV EventsUAV Events

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• Event #4 is technically not part of the recoverysystem but is next in the sequence of events

• Occurs after successful recovery event #2 at 1,000 ft(altimeter controlled black powder ejection of the sabotwith full deployment of the UAV from that hinged-on-one-end sabot via spring pressure from the bendable wing)• Full UAV deployment is visually validated

• Wings have fully unrolled• UAV is not tangled in shroud lines or shock cords• Appears to try to fly away from the parachute• Is safely away from spectators• UAV is at or below 400 ft as indicated on the ground station telemetry (per the FAA AC 91-57 “Do not fly model aircraft higher than 400 feet above the surface”)• Range Safety Officer has given the OK

• The UAV is released by command from the ground via the 2.4GHz RC radio via a servo controlled latch

UAV EventsUAV Events

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• The UAV is released from the Sabot via ejection charge under 1000 feet in altitude • The UAV descends on a parachute until it is validated that:

• The UAV is fully deployed and flight-worthy• The UAV is under 400 feet in altitude

• The UAV is then flown down to a landing while under RC control• Real time video data is returned to the ground station during the flight

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Drift During RecoveryDrift During Recovery• Lower Sustainer Section

• I - Drops from 5,280 ft to 950 ft at 66.38 ft/s on 36” drogue• II - Drops from 1,000 ft to 850 ft at 24.89 ft/s on 96” main with the top section weight• III - Drops from 850 ft to 0 ft at 21.21 ft/s on 96” main

• Top Section (with UAV)• I –Drops from 5,280 ft to 950 ft at 66.38 ft/s on 36” drogue• II – Drops from 1,000 ft to 850 ft at 24.89 ft/s on 96” main with the top section weight• III - Drops from 850 ft to 0 ft at 19.49 ft/s on 48” parachute

• UAV (if not separated from parachute)• I – Drops from 5,280 ft to 950 ft at 78ft/s on 36” drogue• II – Drops from 1,000 ft to 850 ft at 24.89 ft/s on 96” main with the top section weight• III - Drops from 850 ft to 0 ft at 19.99 ft/s on 24” parachute

Lower Sustainer Section

Wind (MPH)

Wind (ft/s)

I - Drogue Range (feet)

II - Main Range (feet)

III - Main Range (feet)

Total Range (feet)

0 0.00 0 0 0 05 7.33 486.79 182.53 155.54 824.85

10 14.67 973.57 365.05 311.08 1649.71

15 22.00 1460.36 547.58 466.62 2474.56

20 29.20 1947.14 730.11 622.16 3299.41Top Section

Wind (MPH) Wind (ft/s)



III – Top Parachute Range (feet)

0 0.00 0 0 0

5 7.33 486.79 182.53 131.63

10 14.67 973.57 365.05 263.27

15 22.00 1460.36 547.58 394.90

20 29.20 1947.14 730.11 526.53

Top Section

Wind (MPH)

Wind (ft/s)



III – UAV Range (feet)

0 0.00 0 0 05 7.33 486.79 182.53 146.5910 14.67 973.57 365.05 293.1915 22.00 1460.36 547.58 439.7820 29.20 1947.14 730.11 586.37

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Configuration of Configuration of the HCXthe HCX

Flight ComputerFlight Computer

HCX Provides 4 Pyro Ports• Pyro 1 – Not Used• Pyro 2 – Drogue deployment via black powder charge at Apogee + 2.0 seconds for Mach Delay• Pyro 3 – UAV deployment via black powder charge at 800 feet •Pyro 4 –Main deployment via Tender Descender black powder charge at 1000 feet

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Configuration of Configuration of the Raventhe Raven

Flight ComputerFlight Computer

The Raven Provides 4 Pyro Ports• Pyro 1 – Drogue deployment via black powder charge at Apogee + 2.0 seconds for Mach Delay• Pyro 2 – Main deployment via Tender Descender black powder charge at 900 feet•Pyro 3 – UAV deployment via black powder charge at approximately approximately 750 feet •Pyro 4 – Not Used

GPS TRACKINGGPS TRACKING

Beeline receives GPS positionBeeline receives GPS position• Encodes as AX.25 packet dataEncodes as AX.25 packet data• Sends as 1200 baud audio – 1 at each end of 70 cm ham bandSends as 1200 baud audio – 1 at each end of 70 cm ham band

VX-6R switched between two frequencies and extracts audioVX-6R switched between two frequencies and extracts audio TinyTrack 4 converts audio to digital NMEA location dataTinyTrack 4 converts audio to digital NMEA location data Garmin displays the digital location data on human screenGarmin displays the digital location data on human screen

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Transmitters in Vehicle

• Big Red Bee Beeline GPS• RF: 17mW on 70cm ham band• Battery and life: 750mAh 10 Hrs• Size: 1.25” x 3” 2 ounces

Ground Station

• Receiver: Yaesu VX-6R• TNC: Byonics Tiny Track 4• GPS: Garmin eTrex Legend

Payload/Vehicle IntegrationPayload/Vehicle Integration

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• UAV is encased in a sabot• Protects the UAV from ejection charge• Provides a clean method for deploying the vehicle from the body tube• Sabot is pushed out by a piston

• Deployment and flight plan• Ejection before main at 900 ft• UAV will descend under parachute until verified flight-worthy and under 400 ft• Parachute will be released• UAV will fly under RC control

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Lessons LearnedLessons Learned1 Always Ground Test

2 What works for someone will not necessarily work for someone else

3 It is a lot easier to correct errors on the scale model than the full scale model

4 Modifying a RC plane is a lot harder than it looks

5 Allow plenty of time

6 This is a huge, huge project

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Status Status UAV UAV is flying, but is hard to control – working

to resolve

Main Parachute

Deployment of the main parachute is not smooth – working to resolve

Wingless UAV

Deployment is smooth and complete

Next Launch 4/14

Will test final resolution of open items

Initial Project We plan to finish the initially proposed project during the summer

RisksRisks

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5 Risk: The rocket weather cocks

10 Risk: The Rocket lands in mud

15 Risk: A parachute misfires

20 Risk: The tracking device isn’t accurate

25 Risk: The UAV hits an object

30 Risk: The battery(s) of our electronics bay fall out

4 Risk: The engine “chuffs”

9 Risk: The rocket lands in a dangerous area

14 Risk: The batteries die during launch

19 Risk: A servo cable on the UAV catches

24 Risk: A part or battery disconnects

29 Risk: No recovery system

3 Risk: the rocket struggles off the launch pad

8 Risk: Interference of the lawmate video transmitter and xbee telemetry

13 Risk: a parachute fires at the wrong alititude

18 Risk: The electronics in the UAV over heat

23 Risk: Sheer pins aren’t put in place

28 Risk: Loss in signal via controller

2 Risk: The rocket folds upon itself

7 Risk: The parachute tangles around the UAV

12 Risk: The engine explodes

17 Risk: The UAV Motor propeller breaks during sabot release

22 Risk: Tracking device is damaged in launch

27 Risk: The black powder is not the correct amount

1 Risk: rocket misfires Mitigation: check continuity

6 Risk: The Parachute doesn’t detach from the UAV

11 Risk: The Rocket’s fins break

16 Risk: The altimeters aren’t set to fire the parachutes

21 Risk: Tracking device doesn’t transmit radio waves

26 Risk: The electric match doesn’t ignite the black powder

Risks MitigationRisks Mitigation

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5 Mitigation: the design is not over stable

10 Mitigation: Make sure launch site is dry

15 Mitigation: double check programming on the altimeter is correct

20 Mitigation: Make sure tracking device works

25 Mitigation: UAV can be switched from autopilot to manual mode Each member in the payload subsection will know how to fly the UAV

30 Mitigation: zip tie batteries and double check connection

4 Mitigation: make sure igniter is all the way in the engine

9 mitigation: Launch site is clear of all hazardous materials

14 Mitigation: use fresh batteries

19 Mitigation: test the cables before flight and have a large enough opening

24 Mitigation: use strong connectors and zip ties to secure wires

29 Mitigation: Double-check our rocket is set up correctly

3 Mitigation: use the correct size launch rod

8 Mitigation: Make sure that the frequencies do not interfere with one another


18 Mitigation: Air vents will be placed for the entering and exiting of air – this will provide enough ventilation

23 Mitigation: double check the rocket before placing on the launch pad

28 Mitigation: using a 2.4GHZ radio for long range and less interferences

2 Mitigation: body tube and nose cone are fiberglass

7 Mitigation: Make sure the parachute is correctly folded

12 Mitigation: make sure there is no defects in engine

17 Mitigation: A folding propeller will be used – this opens up when the motor powers on.

22 Mitigation: Make sure Tracking device is secure and is fully encased in the Styrofoam

27 Mitigation: have a backup charge to either “blow it out or blow it up”

1 Mitigation: check continuity

6 Mitigation: Check harnesses and linkages

11 Mitigation: Use in wall fins


21 Mitigation: double check tracking device is on

26 Mitigation: make sure there electric match is touching the black powder

SafetySafety

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• Follow NAR and TRA safety rules for launch• Safe material usage restrictions• Safe distance from launch pad• Safe recovery area• Inspection by range safety officer before flight

• Follow our check list when preparing for launch• Have fire extinguisher and first aid kit on site• Follow our own (AIAA OC Section Rocketry) safety rules for shop• MSDS referred to as needed (can be found on our web site)• Manuals are posted on the web site since they contain set-up information for recovery electronics• Presentation given to all team members with their signature that they attended and understand

Educational OutreachEducational Outreach

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• Space 2011 Education Alley (Sept – too early for credit) • Girl scout workshop and launch outing in October/November 2011• Talk at St Norbert school January 2012• Talk at Montesorri school in Fullerton January 2012• Have a STEM booth at Science Night at La Habra Elemetry school March 2012• Newspaper articles

• Article in Sunny Hills High School (Fullerton, CA) school paper• Submitting an article for the local local paper in Orange, CA – The Foothills Sentry

• Presentations at Orange County 4H clubs• Youth Expo at the Orange County Fair Grounds April 2012• Present at the AIAA ASAT Conference in May

Budget - ExpendituresBudget - Expenditures

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Budget – IncomeBudget – Income

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• NASA Grant for SLI teams• Fundraising letters (very disappointing)

• Boeing• Raytheon• Northrop Grumman• Lockheed Martin• Thirty other aerospace related companies

• Sees candy sales (moderately successful)• Beg for support from parents

TimelineTimeline

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Thank you for letting us Thank you for letting us be part of SLI againbe part of SLI again

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Questions?Questions?

STUDENT LAUNCH INITIATIVE 2011 – 2012 AIAA OC Rocketeers FRR Presentation April 9, 2012

Documents

Transcript of STUDENT LAUNCH INITIATIVE 2011 – 2012 AIAA OC Rocketeers FRR Presentation April 9, 2012