Madison West High School Green Team

Madison West High School Green Team

The Effect of Gravitational Forces on Arabidopsis Thaliana Development Flight Readiness Review

The Vehicle

Mission Performance Criteria Successful two stage flight Altitude of one mile reached accurately Successful recovery of both stages Payload not damaged Successful collection of acceleration profile

Vehicle Design A Rocket design drawing with CP and CG marked (sustainer CP: 59 inches, liftoff CP: 95 inches (from the tip of the nosecone)). A 3D model of the rocket. The red sections indicate where the electronics will be located. The payload will be placed in the green sections. The recovery systems for both stages are above the payload in each stage to allow each stage to descend in the upside up manner.

Changes to Design 6 fins for the booster (to move the CP down and eliminate need for noseweight) Longer booster (to make enough space for recovery subsystem) Those two changes resulted in lesser sensitivity to wind speed (only 600ft difference over the 0-200 mph wind speed range).

Overall Vehicle Scheme Sustainer High g s (35+) Supersonic Dual deployment Drogue in apogee Main at 500ft LEGEND Drogue Parachute Alt/Acc/Timer/RDAS Biological Payload Main/PYL Parachute Motors Walston TX (Tracking) Booster Low g s (5-10) Single deployment Timed staging Timed deployment

Flight Sequence Flight Sequence

Update Drawing Stage Coupling Transition Legend 4. Timer for stages separation 1. Stage Coupling Tube 5. Charge for separation 2. Motor Mount for second stage 6. Timer for 2 3. Centering Rings nd stage ignition 7. Igniter for 2 nd stage

Electronic Bay Second Stage Electronics Bay Legend 1. Ejection Charge for drogue parachute 2. RDAS and Accelerometer 3. Primary Altimeter 4. Back-up Altimeter 5. Ejection Charge for main parachute 6. Separation Timer 7. Staging Timer

Verification Plan and Status V1: Integrity/robustness test V2: Low altitude test flight V3: Parachute drop test V4: Tension test V5: Prototype flight V6: Functionality test V7: Altimeter ground test V8: Radio signal test V9: Electronic deployment test V10: Ejection test V11: Computer Simulation TESTED More Work Needed

Verification Plan and Status C1: Body C2: Altimeter C3: Accelerometer C4: Parachutes C5: Fins C6: Payloads C7: Timers (for separation and staging) C8: Ejection charges C9: Radio beacon C10: Launch system C11: Motor mount C12: Audio tracking (screamers) Legend P: Planned tests T: In progress F: Finished tests

C 2 C 3 C 4 C 5 C 6 C 7 C 8 C 9 C 10 C 11 C 12 F T F F F T T T F T T F F F F Verification Matrix V V 1 V 2 V 3 V 4 V 5 V 6 V 7 V 8 V 9 V 10 11 C 1 F F F T F T F F F F F F F T T F F Verification Matrix Legend P: Planned tests T: In progress F: Finished tests

Design at System Level Required Subsystems First Stage/Second Stage: Propulsion Structural Payload Bay Deployment Recovery Tracking System

Propulsion System Booster powered by a hybrid K630 motor Sustainer powered by a solid J800T motor Centered by 3 Aircraft ply-wood centering rings Secured by an active retention system (booster: quad L-clamps, L sustainer: Lock N Load Load screw-on ring)

Structural: Design at System Level Booster 6 6 Phenolic tube Sustainer 4 4 Fiberglassed Phenolic tube Payload Bay: Phenolic coupler tube that houses Petri dishes Sealed with plywood caps on both ends Same in both 1 st and 2 nd stage Deployment System: Booster Altimeter for parachute deployment Sustainer 500 ft main Timer for stage Separation (PerfectFlite( PerfectFlite) Two dual event altimeters (PerfectFlite, one as backup) Timer for motor ignition (PerfectFlite( PerfectFlite)

Tracking and Launch Systems Tracking: Walston radio beacon Walston Beacon Receiver (ICOM) Walston Yaggi Antenna (3 elements) Two 140dB screamers Launch System: Ground support equipment for the Hybrid Motor System Launch rail (144 inches long)

Recovery System Single deployment system for first stage Dual deployment system for second stage Parachute Size (in) Descent Rate (fps) Weigh t (lbs) Ejection Charge (g FFF BP) First Stage Main 96 15 11.0 5 w/piston Second Stage Drogue 15 50 5.8 3 w/o piston Second Stage Main+Drouge 70 15 5.8 1 w/piston

Simulation Results With K630/J800T Wind Speed (mph) Apogee (ft) Max Accel (gee's) Max Velocity (mph) Ballast in second stage (lbs) Stability Margins (2 nd Stage/ 1 st Stage) 0 5331 15 460 6.00 2.27/7.45 5 5247 15 461 6.00 2.27/7.17 10 5274 16 494 5.00 2.27/6.96 15 5298 18 517 3.75 2.27/6.78 20 5247 20 550 2.75 2.27/6.45 According to our preliminary results (described in the payload section), 15g stress will be fully sufficient to cause visible changes in the growth of plants. Thus, the rocket does not need to reach the maximum acceleration for the experiment to succeed and we can ballast the sustainer to reach the target altitude.

Flight Profile Simulations Simulated acceleration profile for both stages

Flight Profile Simulations Re: [ROCKET CLUB: SLI2006] CDR Presentation Reminder Altitude vs. Time (wind speed = 10 mph, ballast weight = 6.5 lbs., first stage motor: K630, second stage motor: J800T)

Scale Model Test Flight Results Stable flight of the whole rocket (1:2.6 scale model used). The rocket flies straight even at 15mph wind with the CG located one body diameter above the 2/3 of the booster. Electronic second stage ignition still under development. We will use the PerfectFlite timer with a G-switch G and as of now, we have successfully tested the timer during a single stage flight. A special homemade low resistance igniter will be used to ignite the second stage.

Launch Risk Plot Problem Rocket doesn t stage Faulty Design unstable rocket Faulty Design structural failure First Stage Failure rocket doesn t ignite Result Second half of experiment is not carried out. Unsuccessful flight. Rocket disintegrates. Nothing happens. Mitigation We will do extensive testing of staging mechanisms during prototype and test flights We are doing computer simulations, low altitude flights, and prototype flights to make sure that the rocket is stable Sturdy materials (Kevlar, fiberglass, epoxy, etc.) that can sustain the stresses of the flight will be used. We use the igniters and motors properly so they do ignite.

Launch Risk Plot Launch failure launch rod malfunction Staging Failure catastrophic motor malfunction Recovery Failure parachutes fail to deploy or become tangled Transportation rocket is damaged during transportation Stage Separation Failure- Second stage does not separate from first stage Rocket leaves launch pad at an undesired angle. Rocket explodes. (Severe damage to the rocket and motor casing.) Ballistic fall of rocket and/or payload. Possible aberrations in launch, flight, or recovery First Stage is severely damaged. The plants are destroyed due to exposure to heat. Launch rod will be leveled, lubricated, and secured to a stable surface. Motors are properly stored and used. Parachute will be properly prepared and installed before the launch. Rocket will be properly packaged for transportation and inspected carefully before the launch. The stages will be attached loosely so that they can separate easily.

Launch Risk Plot Timers Do Not Initiate Reaction at the Proper Time Rocket is Carried off by Strong Wind Parachute is Tangled RDAS Failure Stages do not separate and/or parachutes/ drogue do not deploy. Rocket is lost. Mission failure. Unsafe landing of rocket. We would have no acceleration data. Rigorous tests of the timers accuracy will be performed during test flights. A tracking system will be used to locate the rocket. Radio beacon and screamers provide help in finding the rocket. Parachute shock cords will be carefully folded and inserted to prevent entanglement. Test RDAS during test flights and prior to launching to ensure that it is functioning properly before being inserted in the rocket. Insert fresh batteries prior to launch.

Payload Integration Payload consists from stacks of Petri dishes housed in a coupler tube. The payload fits snugly in the second stage 4 4 body. The first stage body is larger and 4 4 payload housing will be centered inside the tube by two centering rings. The electronics will be housed in standard e-e bays built out of a coupler tube and plywood caps.

Final Assembly Procedures 1. Check structural integrity of rocket 2. Attach parachutes to shock cords and attach shock cords to rocket sub assemblies 3. Assemble and insert the first payload into the first stage assembly 4. Insert parachutes into the first stage assembly 5. Assemble and insert the second payload into the second stage assembly 6. Insert parachutes into the second stage assembly 7. Assemble the rocket 8. Assemble the re-loadable motor 9. Insert and secure motor into the motor mount

First Stage Final Assembly Procedures 1. Load the payload capsule gently into the first stage body tube. 2. Verify that the first stage electronics (MAWD altimeter) is functional and have the correct settings and disarm electronics. 3. An adult will prepare an ejection charge for the electronic deployment of the first stage parachute. 4. Attach the ejection charge to electronics bay (e-bay) terminal. 5. Insert first stage e-bay e on top of payload with the e-bay e terminal and ejection charge on top. 6. Place the rest of the first stage body tube on the e-bay e and secure the e-bay e to the first stage body with screws. 7. Attach the first stage parachute s s shock cord to the hook on the e-bay, e insert the shock cord in the body tube in the proper manner and place folded first stage parachute on top.

Second Stage Final Assembly Procedures 1. Load the payload capsule into the upper stage body tube. 2. An adult will prepare an ejection charge with two electronic matches and put them in the rocket with their wire hanging out of the tube. 3. Attach shock cord to the top of the payload capsule, insert the cord in the proper manner, and place the second stage main parachute on top of the shock cord and ejection charge. 4. Verify the electronics (RDAS, altimeters, and timer) are functional nal and have the correct settings and disarm electronics. 5. An adult will prepare another ejection charge with two electronic c matches. 6. Attach one wire from each ejection charge to each altimeter. 7. Place the e-bay e onto the second stage body tube with the second ejection charge and the terminal on top. 8. Attach the drogue parachute shock cord to the hook on the e-bay. e 9. Put in the parachute in the proper manner. 10. Put on the nosecone.

Propulsion Systems Motor Preparation The motors will be prepared by Scott Goebel, our NAR mentor. The motors are solid fuel J for the upper stage and a hybrid K for the lower stage, they will be assembled and prepared in their respective motor mounts by Mr. Goebel. Throughout these motor preparation procedures, all the electronics in the rocket will be disarmed.

Pre-Launch Procedures 1. Place assembled rocket on launch rail 2. Active payload electronics 3. Activate altimeter to arm the ejection charges 4. Activate separation/staging electronics 5. Insert igniter into the assembled motor 6. Connect igniter to the launch system 7. Check continuity 8. Check sky for aircraft 9. Arm ignition system 10.Countdown 11.Launch

Post-Flight Inspection Post Flight Inspection 1. Make sure all charges have fired during flight. 2. Deactivate all electronics and sonic beacons. 3. Remove payload and check for damage. 4. Download data from the RDAS and altimeters. 5. Let the motor casings cool down and then remove from rocket, checking for damage.

Disarming and Re-arming Procedure 1. Remove ignition interlock to prevent accidental ignition 2. Wait designated time by HPR safety code (1 minute) 3. Disarm electronics and remove rocket from pad 4. Reinstall igniter 5. Place rocket back on pad, re-arm electronics 6. Test continuity

Safety NAR safety codes will be observed A safety briefing will be conducted prior each launch Procedure and safety code knowledge of all members will be test on regular basis All devices will be used in the accordance with manufacturers instructions and the operational manuals for all devices will be always on hand All electronics will have arming switches Only a certified mentor will handle the motors and ejection charges Safety equipment will be used as required

Major Milestone Schedule April 2006 8th Two stage flight with payload, 1 mile altitude 9th 1 mile altitude test flight evaluated, improvements to design and to payload suggested 14th Design improvements and changes finished 23rd Last repairs and improvements start 28th Rocket ready for final SLI Launch May 2006 3rd 7th SLI Final Meet/Launch in Huntsville

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The Payload

PAYLOAD OBJECTIVE The goal of the payload is to observe how Arabidopsis thaliana seedlings react to the strong, sudden forces associated with the acceleration of a rocket launch.

EXPERIMENTAL VARIABLES Six different data groups will be tested: Two genetic types of seedlings will be subjected to three different accelerations. Seed Lines Wild Type Agravitropic Acceleration Control Booster Sustainer

PAYLOAD OUTLINE 3-44 days post-germination Plants will be subjected to two brief jolts of acceleration during launch Short and long-term developmental effects of acceleration will be tested

EXPERIMENTAL RATIONALE Measures potential sources of error in launching biological payloads for space missions Conventional acceleratory-forces studies are longer-term, lower-intensity, while ours concentrates on short, high-intensity intensity force applications Genetically-designed and -altered plants are increasingly important in plant sciences

ROCKET DATA ACQUISITION SYSTEM Onboard RDAS unit will record acceleration profile Results will be used as estimation of acceleratory forces applied to plants Located in sustainer s s electronics bay Measures within 0.1g; however, dampening effects from agar may somewhat reduce accuracy

ARABIDOPSIS STRAINS Mutant strain will be agravitropic, containing a genetic alteration reducing sensitivity to gravity & acceleratory forces Other strain will be normal ( wild( type ) plants Both strains used will contain a genetic marker that facilitates root growth analysis (gene marker DR5-GUS)

PAYLOAD STRUCTURE 4 Petri dishes with MS Media nutrient agar 2.5 % solution, 10mL per dish 15 seeds will be placed on each dish one strain per dish Spacing between seeds will be maximized

RISK ASSESSMENT Significant Risks Table RISK Petri dish contamination Low seed germination rate Traumatic damage to seedlings during flight MITIGATION Aseptic technique Preparation of redundant dishes Sturdy construction of seed housings

PAYLOAD BAY STRUCTURE EXPLODED VIEW Bulkhead Single Petri dish ASSEMBLED VIEW

OVERALL PAYLOAD STRUCTURE PAYLOAD LOCATION LEGEND Petri dishes containing both strains of Arabidopsis will be placed in three locations. Sustainer Payload Section (~40g) Booster Payload Section (7g) Control Plants (non-flying) PLANT STRAINS Unaltered Plants Agravitropic Plants

PAYLOAD SUCCESS CRITERIA CHECKLIST Survival rate of at least 50% RDAS records accurate data Each stage reaches distinct acceleration Petri dishes remain sterile, undamaged Integration modules remain intact

APPROACH TO WORKMANSHIP Aseptic technique Contaminant prevention Close supervision

RESULTS ANALYSIS TECHNIQUE 1/3 MICROSCOPIC ANALYSIS Microscopic root analysis will be employed to obtain a detailed picture of root structure and discern the presence of traumatic damage to cells. We will use standard light microscopes as well as high- resolution dissecting scopes (on loan from the University of Wisconsin).

RESULTS ANALYSIS TECHNIQUE 2/3 GENE MARKER ANALYSIS When a stain is applied to the plants, cells containing the genetic marker DR5-GUS are identified. These cells are root growth promoters called auxins, allowing us to visually track root growth under a dissecting scope. Blue stain applied

RESULTS ANALYSIS TECHNIQUE 3/3 LONG-TERM GROWTH ANALYSIS Post-launch, approximately 1/3 of the seeds from each strain and section will be grown to maturity. After they reach the maximum development possible within the Petri dishes, they will be transferred to nutrient-enriched enriched soil. Frequent observations, comparing each type of plant to the control, will be made in order to track any alterations caused by the launch.

PLANT GROWTH PROCEDURES One week prior to launch, 8 dishes each of wild type and agravitropic seeds will be plated with 15 seeds After growing under lights until the launch date, the 12 healthiest dishes will be installed in the integration modules Post-launch, all dishes will be transferred back to growing conditions Schematic of booster integration module

MARCH 25 TEST FLIGHT Sustainer was flown with J800T engine Four Petri dishes of 20 wild-type plants each were prepared 5 days prior to launch Two dishes remained on ground as controls, two were flown Sustainer reached 37.5g (barometric data) Payload was recovered successfully

MARCH 25 TEST FLIGHT FLOWN PLANTS CONTROL PLANTS

PAYLOAD TEST FLIGHT SYNOPSIS Launched one-week week-old Arabidopsis Extremely harsh stress Caused visible duress Discerned with surprising promptness

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