Preliminary Design Review

1. PROJECT BAMBOO Preliminary Design Review A Comprehensive Study of Healing of Fargesia Fungosa from Hypergravity Induced Damage

2. Part I: Vehicle

3. March 20 Two stage rocket test flight April 14 – 15 Rocket fair and safety check April 16 SLI launch Day Major Milestone Schedule

4. Mission Profile Chart • 1) Launch, First stage burn • 2) Stage separation • Sustainer burn • 2a) Booster apogee, parachute • deployment • Sustainer apogee, drogue • deployment • 5) Sustainer descends under drogue • 3a) Booster touchdown • Sustainer main deployment, descent • 7) Sustainer touchdown

5. Stable launch of the vehicle Target altitude of one mile reached Smooth stage separation Second stage ignition Proper deployment of all parachutes Safe recovery of the booster and the sustainer Vehicle Success Criteria

6. Entire Vehicle • CP134” (from nosetip) • CG105” (from nosetip) • Static Margin9.2 calibers Length185” Diameter 3” Liftoff weight29 lb (13 kg) MotorsCTI Pro54 J1055-Vmax (booster), CTI Pro54 K2045-Vmax (sustainer)

7. Sustainer • CP93” (from nosetip) • CG71” (from nosetip) • Static Margin7.1 calibers Length109” Diameter 3” Liftoff weight16.5 lbs (7.5 kg) Motor CTI Pro54 K2045-Vmax

8. Vehicle Schematics

9. Fins: 1/8” G10 fiberglass mounted TTW Body: fiberglass tubing, fiberglass couplers Bulkheads: 1/2”plywood Motor Mounts: 54mm phenolic tubing, 1/2” plywood centering rings Nosecone: commercially made plastic nosecone Rail Buttons: Large nylon rail buttons Motor Retention system: Aeropack screw-on motor retainer Anchors: 1/4” stainless steel U-Bolts Epoxy: West System with appropriate fillers Construction Materials

10. Motor Selection Booster

11. Motor Selection Sustainer

12. Thrust Curve

13. Acceleration Profile

14. Velocity Profile

15. Altitude Profile

16. Wind Speed vs. Apogee

17. Flight Safety Parameters

18. Wp - ejection charge weight in pounds. dP - ejection charge pressure, 15psi V - 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 Ejection Charge Calculations Wp = dP * V / (12 * R * T)

19. Calculated Ejection Charges Ejection charges were verified by static testing. We are using Triple Se7en Pyrodex for ejection charges (the charges are wrapped to ensure proper pressurization).

20. Parachutes

21. Drift Predictions

22. Electronics Two main ejection charges One separation charge • All ejection systems are independent and fully redundant • The sustainer is ignited by two redundant M-Tek e-matches with a pyrodex pellet • The igniters and separation charge are fired by PerfectFlite timers activated by a g-switch • The separation charge fires at booster burnout, 0.1 seconds before the sustainer ignition • All electronics and charges are redundant except for the separation charge Two sustainer igniters Two ejection charges Two drogue ejection charges

23. Tested Components C1: Body (including construction techniques) C2: Altimeter C3: Data Acquisition System (custom computer board and sensors) C4: Parachutes C5: Fins C6: Payload C7: Ejection charges C8: Launch system C9: Motor mount C10: Beacons C11: Shock cords and anchors C12: Rocket stability C13: Second stage separation and ignition electronics/charges Verification Plan

24. Verification Tests V1 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 durability V4 Prototype Flight: testing the feasibility of the vehicle with a scale model. V5 Functionality Test: test of basic functionality of a device on the ground V6 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 Plan

25. Verification Matrix

26. Full Scale Vehicle Launch

27. Test rocket robustness and stage coupling Test full deployment scheme Test second stage ignition Test validity of simulation results Determine necessary altitude adjustments (ballast) Full Scale Vehicle Launch Objectives

28. Flight Data Turbulence from motor explosion Main ejection Apogee event

29. Motor: J1299N Apogee: 644 ft. Time to apogee: 4.5 seconds Apogee events: Drogue parachute ejection Main Events: Main Parachute Ejection Flight Results AT-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.

30. Parachute Measured Descent Rates Unfortunately because of the low apogee, we have no data for the sustainer descent under the drogue parachute.

31. Lessons Learned

32. 03/26: Upcoming Test Flight We 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).

33. Part II: Payload

34. To investigate the effects of hypergravity on the growth, structural changes and healing of Fargesia Fungosa seedlings Payload Objectives

35. Bamboo grown to specified length Successful application of acceleration forces on bamboo Undamaged payload Reliable data from electronics Maintain experimental controls Successful post-flight analysis Payload Success Criteria

36. Bamboo 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 modules Bamboo shoots in the booster and sustainer experience high gravitational forces vertically or horizontally Samples collected each day and analyzed for changes in cell structure and growth patterns Data tabulated and graphed after 3 weeks Final report written Experiment Sequence

37. Payload 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

38. A 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 Sustainer Payload Booster Payload

39. Integration Feasibility The 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.

40. 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 System Inter-Payload Bulkhead Tie Rods Polycarbonate Tube

41. Biological System • FargesiaFungosawill be used as the bamboo species • After 1 week of growth, the bamboo will be flown for the experiment

42. The loam mixture will provide nutrients for the bamboo, as well as structural support. Bamboo (FargesiaFungosa) are planted into the loam The Loam Containment Unit will be used to contain the loam and the FargesiaFungosain the horizontally oriented chambers. Biological System LCU Loam Bamboo (FargesiaFungosa)

43. Data Acquisition Humidity sensor Analog-digital converter Thermistor Microcontroller Light sensor Nonvolatile memory

44. Central Board’s Schematic

45. Data Acquisition • Sampling Locations: • Light, humidity, and temperature sensors on each of the satellite boards in each environmental chamber • Accelerometers/altimeters in the electronics bay • Sampling Rate: • Light, humidity, and temperature are sampled at 1Hz frequency • Accelerometer samples at 100Hz with 8x oversampling • Altimeter samples at 100Hz with 8x oversampling

46. Data Acquisition The payload will measure the temperature, humidity, and light inside each Environmental Chamber Central flight computer will provide timeline, altitude and acceleration information Central Board ADC analog-digital converter B pressure sensor BATT battery CPU microprocessor C connector Ep EEPROM GG-switch H humidity sensor L LED illumination Ls light sensor Pc power connector Tthermistor Satellite Boards

47. Data Acquisition • Each environmental chamber has dedicated satellite board • Each set of 4 environmental chambers (1 in booster, 1 in sustainer) has dedicated payload computer • Each satellite board sends data to payload computer • Central computer logs data in non-volatile memory

48. Experimental Procedure

49. 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 4 Day 4 Growth Plant 3 Day 3 Growth Plant 2 Day 2 Growth Plant 1 Day 1 Growth

50. Postflight Procedure