Preliminary Design Review A Comprehensive Study of Healing of Fargesia Fungosa from Hypergravity Induced Damage

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

2. Part I: Vehicle

3. December 11 Begin work on scale model January 2 Scale model completed January 15 Scale model test flight February 13 Full scale vehicle completed February 20 Sustainer test flight March 13 Two stage rocket test flight March 22 Payload 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 • CP 127” (from nosetip) • CG 104” (from nosetip) • Static Margin 7.3 calibers Length 180” Diameter 3” Liftoff weight 30 lb (13 kg) MotorsJ800T (booster), J1999N (sustainer)

7. Sustainer • CP 87” (from nosetip) • CG 63” (from nosetip) • Static Margin 7.5 calibers Length 107” Diameter 3” Liftoff weight 17 lbs (7 kg) Motor J1999N

8. Vehicle Schematics

9. Fins: 1/32” G10 fiberglass + 1/8” balsa sandwich, 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: standard 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. Apogee vs. Windspeed

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 will be verified in static testing when the vehicle is fully constructed.

20. Parachutes

21. Drift Predictions

22. 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

23. 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

24. Verification Matrix

25. Part II: Payload

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

27. 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

28. 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

29. Payload 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

30. 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

31. 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

32. The 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 System Groove Vessel Bulkhead

33. 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 System Bamboo (FargesiaFungosa) Agar Gel

34. 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 System Agar Containment Unit

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

36. 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

37. 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 CPUmicroprocessor C connector Ep EEPROM GG-switch H humidity sensor L LED illumination Ls light sensor Pc power connector Tthermistor Satellite Boards

38. 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

39. Experimental Procedure

40. 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

41. Postflight Procedure

42. Independent Variables A Acceleration T Time elapsed after flight Dependent Variables G Bamboo growth R Bamboo robustness CR and CA Changes in cross section (radial and axial) D Resulting plant density GE Gene expression HHemicellulose concentration L Lignin concentrations Z Rhizome testing Variables

43. Light Exposure Bamboo Specimen Growing Conditions Testing Methods Bamboo Orientation in Payload Chambers Controls

44. Structural Correlations G = f (A, T) Bamboo Growth R = 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 Correlations GE = f (A, T) Gene Expression H = f (A, T) Hemicellulose Concentration L = f (A, T) Lignin Concentration Z = f (A, T) Rhizome Testings Correlations

45. Commercially available sensors will be used Sensors will be calibrated Extensive testing will be done on ground Instrumentation and Measurement

46. Test and Measurement

47. Tested Components C1: Vessel C2: Inter-Payload Bulkhead C3: Agar Gel C4: Fargesia Fungosa (Bamboo Seedlings) C5: Agar Containment Unit C6: Master Flight Computer Storage Subsystem C7: Cable and Data Transfer C8: Power Source C9: Temperature Sensor C10: Humidity Sensor C11: Light Sensor C12: Light Source Verification:Components

48. Verification Tests V1. Drop Test V2. Connection and Basic Functionality Test V3. Pressure Sensor Test V4. Scale Model Flight V5. Temperature Sensor Test V6. Durability Test V7. Battery Capacity Test V8. Final Test Verification: Tests

49. Verification Matrix

50. Outreach Plan