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Preliminary Design ReviewA Comprehensive Study of Healing of Fargesia Fungosa from Hypergravity Induced Damage PROJECT BAMBOO

1Part I: Vehicle

2March 20Two stage rocket test flight

April 14 15 Rocket fair and safety check

April 16SLI launch DayMajor Milestone Schedule31) Launch, First stage burn 2) Stage separationSustainer burn2a) Booster apogee, parachute deploymentSustainer apogee, drogue deployment5) Sustainer descends under drogue3a) Booster touchdownSustainer main deployment, descent7) Sustainer touchdownMission Profile Chart

4Stable launch of the vehicle Target altitude of one mile reachedSmooth stage separationSecond stage ignitionProper deployment of all parachutesSafe recovery of the booster and the sustainerVehicle Success Criteria5Length 185Diameter3Liftoff weight29 lb (13 kg)MotorsCTI Pro54 J1055-Vmax (booster), CTI Pro54 K2045-Vmax (sustainer)CP134 (from nosetip)CG105 (from nosetip)Static Margin 9.2 calibers

Entire Vehicle

6Length 109Diameter3Liftoff weight16.5 lbs (7.5 kg)Motor CTI Pro54 K2045-VmaxCP93 (from nosetip)CG71 (from nosetip)Static Margin 7.1 calibers

Sustainer7LetterPartLetterPartANoseconeHSustainer Motor Mount and Interstage CouplerBSustainer Main Parachute IBooster ParachuteCSustainer E-BayJBooster EbayDSustainer Drogue ParachuteKBooster PayloadESustainer PayloadLBooster FinsFTelemetry/Staging ElectronicsMBooster Motor MountGSustainer FinsVehicle Schematics

8Fins: 1/8 G10 fiberglass mounted TTWBody: fiberglass tubing, fiberglass couplersBulkheads: 1/2 plywood Motor Mounts: 54mm phenolic tubing, 1/2 plywood centering rings Nosecone: commercially made plastic noseconeRail Buttons: Large nylon rail buttonsMotor Retention system: Aeropack screw-on motor retainerAnchors: 1/4 stainless steel U-BoltsEpoxy: West System with appropriate fillersConstruction Materials9Motor Selection BoosterMotorLength [mm]Diameter [mm]Average Impulse [N]Total Impulse [Ns]Burn Time [s]CTI-J1055 V-max2365410577470.73Length[in]Mass[kg]Diameter [in]Motor SelectionStability Margin [calibers]Thrust to weight ratio18313.23CTI-J10559.28.1

10Motor Selection SustainerMotorLength [mm]Diameter [mm]Average Impulse [N]Total Impulse [Ns]Burn Time [s]CTI-K2045Vmax40454204514080.73Length [in]Mass[kg]Diameter [in]Motor SelectionStability Margin [calibers]Thrust to weight ratio1097.53CTI-K20457.126

11Thrust Curve

12Acceleration Profile

13Velocity Profile

14Altitude Profile

15Wind Speed[mph]Altitude[ft]Percent Change in Altitude052500.00%552440.11%1052260.44%1551990.94%2051671.52%Wind Speed vs. ApogeeBoosterSustainerFlight Stability Static Margin9.37.1Thrust to Weight Ratio

8.126Velocity at Launch Guide Departure: 54 mph(launch rail length 144)Flight Safety Parameters17Wp - ejection charge weight in pounds. dP - ejection charge pressure, 15psiV - free volume in cubic inches. R - combustion gas constant, 22.16 ft-lbf/lbm R for FFFF black powder.T - combustion gas temperature, 3307 degrees R

Wp = dP * V / (12 * R * T)Ejection Charge Calculations18Ejection charges were verified by static testing. We are using Triple Se7en Pyrodex for ejection charges (the charges are wrapped to ensure proper pressurization). SectionEjection ChargeBooster (Main)

2.8 gSustainer (Drogue)2.0 gSustainer (Main)2.8 gStage Separation Charge1.0 gCalculated Ejection Charges19ComponentWeightParachute DiameterDescent RateBooster189 oz.60 in.(main)18 fpsSustainer 244 oz.14 in.(drogue)90 fpsSustainer244 oz.60 in.(main)20 fpsParachutes20Drift Predictions Wind speed vs. Rocket driftWind speed [mph]Booster drift [ft]Sustainer drift [ft]0005621576101243115215186517282024872304All ejection systems are independent and fully redundantThe sustainer is ignited by two redundant M-Tek e-matches with a pyrodex pelletThe igniters and separation charge are fired by PerfectFlite timers activated by a g-switchThe separation charge fires at booster burnout, 0.1 seconds before the sustainer ignitionAll electronics and charges are redundant except for the separation charge

Two main ejection chargesTwo drogue ejection chargesTwo sustainer ignitersOne separation chargeTwo ejection chargesElectronicsTested ComponentsC1: Body (including construction techniques)C2: AltimeterC3: Data Acquisition System (custom computer board and sensors)C4: ParachutesC5: FinsC6: PayloadC7: Ejection chargesC8: Launch systemC9: Motor mountC10: BeaconsC11: Shock cords and anchorsC12: Rocket stabilityC13: Second stage separation and ignition electronics/chargesVerification Plan23Verification TestsV1 Integrity Test: applying force to verify durability.V2 Parachute Drop Test: testing parachute functionality.V3 Tension Test: applying force to the parachute shock cords to test durabilityV4 Prototype Flight: testing the feasibility of the vehicle with a scale model.V5 Functionality Test: test of basic functionality of a device on the groundV6 Altimeter Ground Test: place the altimeter in a closed container and decrease air pressure to simulate altitude changes. Verify that both the apogee and preset altitude events fire. (Estes igniters or low resistance bulbs can be used for verification).V7 Electronic Deployment Test: test to determine if the electronics can ignite the deployment charges.V8 Ejection Test: test that the deployment charges have the right amount of force to cause parachute deployment and/or planned component separation.V9 Computer Simulation: use RockSim to predict the behavior of the launch vehicle.V10 Integration Test: ensure that the payload integrates precisely into the vehicle, and is robust enough to withstand flight stresses.Verification Plan24v 1v 2 v 3v 4 v 5 v 6 v 7v 8 v 9v 10C 1PC 2PC 3P C 4C 5C 6C 7C 8C 9C 10C 11C 12C13Verification Matrix25

Full Scale Vehicle Launch

26Test rocket robustness and stage couplingTest full deployment schemeTest second stage ignitionTest validity of simulation resultsDetermine necessary altitude adjustments (ballast) Full Scale VehicleLaunch Objectives27Flight DataApogee eventTurbulence from motor explosionMain ejectionMotor:J1299NApogee: 644 ft.Time to apogee: 4.5 seconds Apogee events: Drogue parachute ejectionMain Events:Main Parachute EjectionFlight ResultsAT-J1299N motor CATOed. The aft closure was expelled from the casing,while the rest of motor advanced inside the rocket, destroying the fin assembly and damaging electronics bay. Deployment electronics functioned flawlessly. Despite of the low flight apogee, both the drogue and main parachute fully deployed and the rocket sustained NO LANDING DAMAGE.29DescriptionInitial Pointtime, altitudeEnd Pointtime, altitudeDescent RateSustainer Main

13 s, 402 ft30 s, 78 ft19 fpsParachuteMeasured Descent RatesUnfortunately because of the low apogee, we have no data for the sustainer descent under the drogue parachute.

30Lessons LearnedProblemMitigationDue to the extreme pressure inside the motor, the aft closure failed and the motor CATOed during flightWe will no longer use Aerotech Warp9 motors. We have changed our motor selection to CTI Vmax and reported the motor failure to Aerotech (MESS form filled).

03/26: Upcoming Test FlightWe have another test flight scheduled for March 26th, 2011. We will provide updates to our FRR documentation as soon as we can process the data from this launch.

The rocket will fly in two stage configuration with final motor combination (CTI J1055Vmax in booster, CTI K2045Vmax in sustainer).

Part II: Payload

33To investigate the effects of hypergravity on the growth, structural changes and healing of Fargesia Fungosa seedlings

Payload Objectives

34Bamboo grown to specified lengthSuccessful application of acceleration forces on bambooUndamaged payloadReliable data from electronicsMaintain experimental controlsSuccessful post-flight analysisPayload Success Criteria35Bamboo seeds planted in environmental chambers Bamboo shoots grow Modules placed in both booster and sustainer in two orientations Temperature and humidity data continuously recorded in modulesBamboo shoots in the booster and sustainer experience high gravitational forces vertically or horizontallySamples collected each day and analyzed for changes in cell structure and growth patternsData tabulated and graphed after 3 weeksFinal report writtenExperiment Sequence

36Payload components are present in both the sustainer and booster sections and will remain there for the duration of rocket flight. To increase the ease of installation the payload modules will be linked together as one unit.Integration Plan

37A total of eight chambers, four chambers each for horizontal and vertical bamboo, will make up the payload. The first set will fly inside the booster section; the second, inside the sustainer. Integration Plan

SustainerPayload

BoosterPayload38Integration FeasibilityThe payload meets size and weight constraints imposed by the vehicle, and will be able to withstand the stresses of rocket flight. The payload units can slide easily in and out of the rocket. There will be screws to hold the payload in place during flight.

The Structural System is the containment system for our payload. Each Environmental Chamber includes a Vessel, which holds the Biological System.

A 2.50 inch polycarbonate tube, the vessel will contain the Biological System of our payload.

Structural SystemInter-Payload Bulkhead

Polycarbonate TubeTie Rods40Fargesia Fungosa will be used as the bamboo speciesAfter 1 week of growth, the bamboo will be flown for the experimentBiological System

The loam mixture will provide nutrients for the bamboo, as well as structural support.Bamboo (Fargesia Fungosa) are planted into the loamThe Loam Containment Unit will be used to contain the loam and the Fargesia Fungosa in the horizontally oriented chambers.

Biological SystemLoamBamboo(Fargesia Fungosa) LCU42Data Acquisition

HumiditysensorThermistorLightsensorAnalog-digitalconverterMicrocontrollerNonvolatilememory43

Central Boards SchematicData AcquisitionSampling Locations: Light, humidity, and temperature sensors on each of the satellite boards in each environmental chamberAccelerometers/altimeters in the electronics bay

Sampling Rate:Light, humidity, and temperature are sampled at 1 Hz frequencyAccelerometer samples at 100Hz with 8x oversamplingAltimeter samples at 100Hz with 8x oversampling45Data Acquisition

The payload will measure the temperature, humidity, and light inside each Environmental Chamber

Central flight computer will provide timeline, altitude and acceleration informationCentral BoardSatellite BoardsADCanalog-digital converterBpressure sensorBATTbatteryCPUmicroprocessorCconnectorEpEEPROMGG-switchHhumidity sensorLLED illuminationLslight sensorPcpower connectorTthermistor46Each environmental chamber has dedicated satellite boardEach set of 4 environmental chambers (1 in booster, 1 in sustainer) has dedicated payload computerEach satellite board sends data to payload computerCentral computer logs data in non-volatile memoryData AcquisitionExperimental Procedure

Postflight TestingDay 1: collect sample from plant #1 (leftmost), measure the aforementioned variables.

Day 2: collect two samples from plant #2, first sample from the section of the plant that grew during Day #1, second sample from the plant section that grew during Day #2. Carry out the same set measurement as in Day #1, however this time for each sampled section. Remove plant #2 from further observations.

Day 3: use plant #3, same procedure as Day #2, but three sections are sampled (Day #1 growth, Day #2 growth, Day #3 growth). Plant 1Plant 2Plant 3Plant 4Day 1 GrowthDay 2 GrowthDay 3 GrowthDay 4 Growth

Postflight ProcedureTestSpecific Measurements following abovementioned methodsBamboo GrowthLength measurements on bamboo will be made every day for three weeksBamboo RobustnessBreak strength meter will measure robustnessRadial Cross Section changesWe will quantify details from microscope analysis of bamboo cross sections (radial)Axial Cross Section changesWe will quantify details from microscope analysis of bamboo cross sections (axial)Density of bambooWeight and volume measurements taken every day for three weeksIndependent VariablesAAccelerationTTime elapsed after flight

Dependent VariablesGBamboo growthRBamboo robustnessCR and CAChanges in cross section (radial and axial)DResulting plant densityVariables51Light ExposureBamboo SpecimenGrowing ConditionsTesting MethodsBamboo Orientation in Payload ChambersControls52Structural CorrelationsG = f (A, T)Bamboo GrowthR = f (A, T)Bamboo Robustness CR = f (A, T)Cross Section Changes (Radial) CA = f (A, T)Cross Section Changes (Axial) D = f (A, T)Resulting Density of Bamboo Correlations53Commercially available sensors will be usedSensors will be calibratedExtensive testing will be done on groundInstrumentation and Measurement54TestMeasurement TemperatureTemperature will be collected 1x per second by each sensorHumidityHumidity will be collected 1x per secondLightLight will be collected 1x per second

Test and Measurement55Tested Components

C1: VesselC2: Inter-Payload BulkheadC3: LoamC4: Fargesia Fungosa (Bamboo Seedlings)C5: Loam Containment UnitC6: Master Flight Computer Storage SubsystemC7: Cable and Data TransferC8: Power SourceC9: Temperature SensorC10: Humidity SensorC11: Light SensorC12: Light SourceVerification: Components56Verification TestsV1. Drop TestV2. Connection and Basic Functionality TestV3. Humidity Sensor TestV4. Temperature Sensor TestV5. Durability TestV6. Battery Capacity TestV7. Final TestVerification: Tests 57V 1V 2 V 3V 4 V 5V 6V 7C 1C 2C 3C 4C 5C 6C 7C 8C 9C 10C 11C 12Verification Matrix58DateEvent# of participantsNovember 2010Presentation and Launch at Allied Outreach Center15November 2010Wisconsin Youth Organization Presentation and Launch50November 2010Alka Seltzer Rockets at Lincoln Elementary25January 2011Alka Seltzer Rockets at EAGLE School25March 2011Alka Seltzer Rockets at Franklin/Randal and OKeefe School Super Science Saturday, 2 events280April 2011Pneumatic Rockets at EAGLE School15June 2011Lunch & Launch: Madison West Rocketry Public Launch and Potluck50Total Participants (estimate)460Outreach PlanOutreach Moments

Questions?61