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

1Part I: Vehicle

2December 11Begin work on scale modelJanuary 2Scale model completedJanuary 15Scale model test flightFebruary 13 Full scale vehicle completedFebruary 20Sustainer test flightMarch 13Two stage rocket test flightMarch 22Payload test flightApril 14 15 Rocket fair and safety checkApril 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 sustainer

Vehicle Success Criteria5Length 180Diameter3Liftoff weight30 lb (13 kg)MotorsJ800T (booster), J1999N (sustainer)CP127 (from nosetip)CG104 (from nosetip)Static Margin 7.3 calibers

Entire Vehicle

6Length 107Diameter3Liftoff weight17 lbs (7 kg)Motor J1999NCP87 (from nosetip)CG63 (from nosetip)Static Margin 7.5 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: 1/32 G10 fiberglass + 1/8 balsa sandwich, TTWBody: fiberglass tubing, fiberglass couplersBulkheads: 1/2 plywood Motor Mounts: 54mm phenolic tubing, 1/2 plywood centering rings Nosecone: commercially made plastic noseconeRail Buttons: standard 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]AT-J800T3165469712291.8Length[in]Mass[kg]Diameter [in]Motor SelectionStability Margin [calibers]Thrust to weight ratio18013.43AT-J800T7.316.0

10Motor Selection SustainerMotorLength [mm]Diameter [mm]Average Impulse [N]Total Impulse [Ns]Burn Time [s]AT-J1999N31654196212500.6Length [in]Mass[kg]Diameter [in]Motor SelectionStability Margin [calibers]Thrust to weight ratio1077.53AT-J19997.5325

11Thrust Curve

12Acceleration Profile

13Velocity Profile

14Altitude Profile

15Wind Speed[mph]Altitude[ft]Percent Change in Altitude060080.00%559950.21%1059610.78%1559081.66%2058422.76%Apogee vs. WindspeedBoosterSustainerFlight Stability Static Margin7.317.53Thrust to Weight Ratio

6.0025.38Velocity at Launch Guide Departure: 75 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 will be verified in static testing when the vehicle is fully constructed.SectionEjection ChargeBooster (Main)

0.9 gSustainer (Drogue)0.4 gSustainer (Main)1.5 gStage Separation Charge0.4 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]0005621576101243115215186517282024872304Tested 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 Plan22Verification 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 Plan23V 1V 2 V 3V 4 V 5 V 6 V 7V 8 V 9V 10C 1C 2C 3C 4C 5C 6C 7C 8C 9C 10C 11C 12C 13Verification Matrix24Part II: Payload

25To investigate the effects of hypergravity on the growth, structural changes and healing of Fargesia Fungosa seedlings

Payload Objectives

26Bamboo grown to specified lengthSuccessful application of acceleration forces on bambooUndamaged payloadReliable data from electronicsMaintain experimental controlsSuccessful post-flight analysisPayload Success Criteria27Bamboo 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

28Payload components are present in both the sustainer and booster sections and will remain there for the duration of rocket flight. We are looking for a design that will allow for easy installation and removal of the payload. Integration Plan

29A 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

BoosterPayload30The 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 Rods31The bulkheads will serve as a transition between each Environmental Chamber. The vessels will fit into the bulkheads and attached using tie-rods. The electrical system will also be attached to the bulkheads.Structural SystemVessel

BulkheadGroove32

The Agar Gel will provide nutrients for the bamboo, as well as structural support.

Fargesia Fungosa (bamboo seedlings) will be planted in the Agar gel. Once they are a week old, the bamboo seedlings will be flown in our vehicle.Biological SystemAgar GelBamboo(Fargesia Fungosa) 33

The Agar Containment Unit will be used specifically for the Horizontally Positioned Bamboo Chamber. This vessel will contain the Agar Gel and the Fargesia Fungosa.Biological SystemAgar Containment Unit34Data Acquisition

HumiditysensorThermistorLightsensorAnalog-digitalconverterMicrocontrollerNonvolatilememory35Data 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 oversampling36Data 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 connectorTthermistor37Each 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 Testing

Day 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 GrowthPostflight 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 weeksGene ExpressionUse of Polymerase Chain Reaction (PCR) available to us from UW MadisonHemicellulose ConcentrationsHigh Performance Liquid Chromatography (HPLC) analysis Lignin ConcentrationsStress testingRhizome TestingLength measurements on bamboo rootsIndependent VariablesAAccelerationTTime elapsed after flight

Dependent VariablesGBamboo growthRBamboo robustnessCR and CAChanges in cross section (radial and axial)DResulting plant densityGEGene expression HHemicellulose concentrationLLignin concentrationsZRhizome testingVariables42Light ExposureBamboo SpecimenGrowing ConditionsTesting MethodsBamboo Orientation in Payload ChambersControls43Structural 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

Biological CorrelationsGE = f (A, T)Gene Expression H = f (A, T)Hemicellulose Concentration L = f (A, T)Lignin Concentration Z = f (A, T)Rhizome Testings Correlations44Commercially available sensors will be usedSensors will be calibratedExtensive testing will be done on groundInstrumentation and Measurement45TestMeasurement TemperatureTemperature will be collected 1x per second by each sensorHumidityHumidity will be collected 1x per secondLightLight will be collected 1x per second

Test and Measurement46Tested Components

C1: VesselC2: Inter-Payload BulkheadC3: Agar GelC4: Fargesia Fungosa (Bamboo Seedlings)C5: Agar Containment UnitC6: Master Flight Computer Storage SubsystemC7: Cable and Data TransferC8: Power SourceC9: Temperature SensorC10: Humidity SensorC11: Light SensorC12: Light SourceVerification: Components47Verification TestsV1. Drop TestV2. Connection and Basic Functionality TestV3. Pressure Sensor TestV4. Scale Model FlightV5. Temperature Sensor TestV6. Durability TestV7. Battery Capacity TestV8. Final TestVerification: Tests 48V 1V 2 V 3V 4 V 5 V 6 V 7V 8 C 1C 2C 3C 4C 5C 6C 7C 8C 9C 10C 11C 12Verification Matrix49DateEvent# of participantsNovember 2010Presentation and Launch at Allied Outreach Center15November 2010Wisconsin Youth Organization Presentation and Launch50November 2010Alka Seltzer Rockets at Lincoln Elementary25December 2010A-Class Rocket Launch at EAGLE School15January 2011Alka Seltzer Rockets at EAGLE School25March 2011Alka Seltzer Rockets at Franklin/Randal School Super Science Saturday100April 2011Pneumatic Rockets at EAGLE School15June 2011Lunch & Launch: Madison West Rocketry Public Launch and Potluck50Total Participants (estimate)295Outreach Plan

OutreachMomentsRockSim simulations and test flights will aid us in the creation of this two-stage rocketwith the maximum achievable accelerationthat has an apogee altitude close to, but not exceeding, 5,280 ft above ground level. The current simulation results show a maximum altitude above 5,280 ft as a performance cushion because the vehicle and payload weight will likely increase as the project progresses. The rocket will be ballasted for the final flight to ensure that the altitude target of 5,280ft is not exceeded.

Reviewer Feedback Response52

Questions?53