PROJECT BAMBOO. Preliminary Design Review A Comprehensive Study of Healing of Fargesia Fungosa from Hypergravity Induced Damage. Part I: Vehicle. March 20 Two stage rocket test flight April 14 – 15 Rocket fair and safety check April 16 SLI launch Day. Major Milestone Schedule.
Preliminary Design Review
A Comprehensive Study of Healing of Fargesia Fungosa from Hypergravity Induced Damage
April 14 – 15 Rocket fair and safety check
April 16 SLI launch Day
Major Milestone Schedule
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
Liftoff weight29 lb (13 kg)
MotorsCTI Pro54 J1055-Vmax (booster),
CTI Pro54 K2045-Vmax (sustainer)
Liftoff weight16.5 lbs (7.5 kg)
Motor CTI Pro54 K2045-Vmax
Body: fiberglass tubing, fiberglass couplers
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
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)
Ejection charges were verified by static testing. We are using Triple Se7en Pyrodex for ejection charges (the charges are wrapped to ensure proper pressurization).
Two main ejection charges
One separation charge
Two sustainer igniters
Two ejection charges
Two drogue ejection charges
C1: Body (including construction techniques)
C3: Data Acquisition System (custom computer board and sensors)
C7: Ejection charges
C8: Launch system
C9: Motor mount
C11: Shock cords and anchors
C12: Rocket stability
C13: Second stage separation and ignition electronics/charges
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.
Test full deployment scheme
Test second stage ignition
Test validity of simulation results
Determine necessary altitude adjustments (ballast)
Full Scale Vehicle
Turbulence from motor explosion
Apogee: 644 ft.
Time to apogee: 4.5 seconds
Apogee events: Drogue parachute ejection
Main Events: Main Parachute Ejection
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.
Measured Descent Rates
Unfortunately because of the low apogee, we have no data for the sustainer descent under the drogue parachute.
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).
Successful application of acceleration forces on bamboo
Reliable data from electronics
Maintain experimental controls
Successful post-flight analysis
Payload Success Criteria
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
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.
A 2.50 inch polycarbonate tube, the vessel will contain the Biological System of our payload.
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.
The payload will measure the temperature, humidity, and light inside each Environmental Chamber
Central flight computer will provide timeline, altitude and acceleration information
ADC analog-digital converter
B pressure sensor
H humidity sensor
L LED illumination
Ls light sensor
Pc power connector
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).
Day 4 Growth
Day 3 Growth
Day 2 Growth
Day 1 Growth
T Time elapsed after flight
G Bamboo growth
R Bamboo robustness
CR and CA Changes in cross section (radial and axial)
D Resulting plant density
Bamboo Orientation in Payload Chambers
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
Sensors will be calibrated
Extensive testing will be done on ground
C2: Inter-Payload Bulkhead
C4: Fargesia Fungosa (Bamboo Seedlings)
C5: Loam 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
V1. Drop Test
V2. Connection and Basic Functionality Test
V3. Humidity Sensor Test
V4. Temperature Sensor Test
V5. Durability Test
V6. Battery Capacity Test
V7. Final Test