A Comprehensive Study of Healing of Fargesia Furgosa from Hypergravity-Induced Damage

Transcription

1 November 19, 2010 A Comprehensive Study of Healing of Fargesia Furgosa from Hypergravity-Induced Damage Madison West High School Back: Suhas, Max, Peter, Jacob E, Duncan Front: Yifan, Enrique, Jacob K SLI 2011 Preliminary Design Review

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3 Table of Contents Summary of PDR Report... 5 Team Summary... 5 Launch Vehicle Summary... 7 Payload Summary... 7 Changes made since Proposal... 9 Changes made to Vehicle Criteria... 9 Changes made to Payload Criteria... 9 Changes made to Activity Plan... 9 Vehicle Criteria... 9 Design Review at System Level and Required Subsystems Propulsion System Entire Vehicle Sustainer Deployment System :3 Scale Model: Entire Vehicle Scale Model Sustainer Scale Model Deployment System Flight Sequence Performance Characteristics for the System Verification Plan and Status Matrix Legend Rocket/Payload Risks Specific Two Stage Vehicle Risks Scheduling and Facilities Risks Integrity of Design Recovery Subsystem Payload Integration Launch Operation Procedures Launch System and Platform Final Assembly and Launch Procedures Safety and Environment (Vehicle) Safety Officer Risks and Mitigations Physical Risks Rocket/Payload Risks Specific Two Stage Vehicle Risks Toxicity Risks Environmental Concerns

4 Payload Criteria Selection, Design, and Verification of Payload Experiment Design at System Level Payload Systems Mechanical System Biological System Data Processing and Storage System Monitoring Components System Performance Characteristics Verification Matrix Payload Preliminary Integration Precision of Instrumentation, Repeatability of Measurement and Recovery System Payload Concept Features and Definition Creativity and Originality Uniqueness or Significance Suitable Level of Challenge Science Value Payload Objectives Payload Success Criteria Describe Experimental Logic, Approach and Method of Investigation Correlations Test and Measurement, Variables and Controls Constants Show Relevance of Expected Data and Accuracy/Error Analysis Preliminary Experiment Process Procedure Safety and Environment Activity Plan Budget Plan Timeline Proposed Launch Schedule Educational Engagement Community Support Outreach Programs Conclusion

5 Summary of PDR Report Team Summary School Name Madison West High School Title of Project A Comprehensive Study of Healing of Fargesia Furgosa Plants from Hypergravity Induced Damage Educators and Mentors Administrative Staff Member West High School Principal Ed Holmes Madison West High School, 30 Ash St., Madison, WI, Phone: (608) eholmes@madison.k12.wi.us Team Official Ms. Christine Hager, Biology Instructor Madison West High School, 30 Ash St., Madison, WI Phone: (608) ckamke@madison.k12.wi.us Educators and Mentors Pavel Pinkas, Ph.D., Senior Software Engineer for DNASTAR, Inc Norman Way, Madison, WI, Work Phone: (608) Home Phone: (608) Fax: (608) pavelp@dnastar.com Brent Lillesand 4809 Jade Lane, Madison, WI Phone: (608) blillesand@charter.net Jeffrey A. Havlena 118 Richland Lane Madison, WI Phone: (608) JAHAVLENA@wisc.edu -5-

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7 Scientific Consultants Donna E. Fernandez Dept. of Botany, UW-Madison Phone: (608) Simon Gilroy Dept. of Botany, UW-Madison Phone: (608) Patrick H Masson Dept. of Genetics, UW-Madison Phone: (608) phmasson@wisc.edu Section 508 Consultant: Ms. Ronda Solberg DNASTAR, Inc. (senior software designer) 3801 Regent St, Madison, WI rondas@dnastar.com Associated NAR Chartered Section #558 President: Mr. Scott T. Goebel Phone: (262) sgoebel@westrocketry.com WOOSH Wisconsin Organization Of Spacemodeling Hobbyists (WOOSH) is a chartered section (#558) of the National Association of Rocketry. They assist Madison West Rocketry with launches, mentoring, and reviewing. Launch Vehicle Summary A two stage rocket, 3" diameter, 15ft length, J/J class propulsion, will be used to generate two distinct acceleration profiles (high-g and low-g). Each stage will carry a payload of bamboo plants that will be subjected to the flight stresses, mainly the gravitational shocks. Payload Summary We will be investigating the effect of hypergravity on the growth and healing of Fargesia Fungosa shoots. Hypergravity research has been done on various plants in laboratories, but because they are done within centrifuges, rapid acceleration and deceleration cannot be easily produced. Although our rocket will not reach extremely high acceleration values, it will go through a rapid acceleration which cannot be obtained in a centrifuge. After a successful flight we will test -7-

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9 Changes made since Proposal Changes made to Vehicle Criteria The full scale flight is modified to accommodate changes in payload weight estimates. We finalized the design of the 2/3 scale model and parameters of its test flight. Changes made to Payload Criteria We finalized our bamboo species, named fargesia fungosa. Also, we are using four environmental chambers as opposed to two per booster and two for second stage. The reason lies in repetition and extra available space in the rocket. Changes made to Activity Plan There have been no significant changes to the Activity Plan since the SOW. Vehicle Criteria Launch Vehicle Summary The vehicle is 15ft long and has 3-inch tubing in both stages. The booster will be powered by an Aerotech J800T, and should reach 1600ft; the sustainer, powered by an Aerotech J1999, has a projected apogee of 6008ft. The booster will eject a main parachute at its apogee, and the sustainer will use a standard dual-deployment system. Mission statement, requirements, and mission success criteria For a successful mission, the vehicle must reach (but not exceed) 5280ft, deliver the payload, and recover safely. 1. The vehicle carries an innovative scientific payload. The bamboo shoots will fly on board through the two-stage flight trajectory. The post-flight analysis of the bamboo shoots for cell structure damage, gene expression changes, stimulated lignin growth will generate qualitative data for a comprehensive study of bamboo healing from hypergravity induced damage. -9-

10 Figure 1: Horizontally Oriented Bamboo Chamber (right) and Vertically Oriented Bamboo Chamber (left) are shown above; each chamber is equipped with a temperature sensor (T), humidity sensor (H), Data Processing and Storage System (a printed circuit board on top of each chamber), agar, and bamboo shoots. 2. RockSim simulations and test flights will aid us in the creation of a two-stage rocket with a maximum achievable acceleration that 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 safety margin 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. -10-

11 Wind Speed [mph] Figure 2: Altitude vs. TIme Graph Altitude [ft] % % % % % Table 1: Flight Apogee vs. Wind Speed Percent Change in Altitude As shown in the table above, the rocket apogee will not vary significantly with the wind speed. There will be only 2.4% altitude loss in the worst case event (wind speed at the NAR limit of 20mph). 3. Our recovery system electronics will include the following characteristics: a. Redundant altimeters-for safety b. Each altimeter will be equipped with an external arming switch and battery that is not shared with any other electronic device in the rocket. c. Every arming switch for each altimeter will be accessible from the exterior of the rocket, via a secured door on the fiberglass body. d. All arming switches are able to lock in the on position for launch. e. The recovery system is designed to be armed while the rocket is on the pad. f. The vehicle will transport separate electronics for each system: the recovery system and the payload each have independent electronics and power sources. -11-

12 4. RockSim simulation indicate that the rocket will remain subsonic (under Mach 1) for the entire duration of the flight, from the launch to the landing. The data from full scale vehicle test flights will be analyzed to ensure that the vehicle did not exceed speed of sound. Figure 3: Shown above is the Velocity vs. Time graph. Rocket remains subsonic throughout the entire flight, maximum speed is 560mph. 5. The rocket is designed and will be manufactured to be recoverable and reusable. The scientific payload is also designed to be recoverable and reusable, and the landing should cause as little damage as possible to the actual bamboo shoots in order to lessen its effect on the experiment. Both the vehicle and the payload will be able to launch again on the same day with no preceding repairs or modifications to either. 6. Separation at apogee will only involve the deployment of the drogue parachute. Payload components will not deploy at launch, or throughout the flight, thus the drift will be minimal. 7. Dual deployment recovery will be used. -12-

13 Figure 4: The Mission Profile Chart includes the flight sequences for both stages and is described with more detail below -13-

14 Event Time [s] Altitude Triggering Triggering [ft] Condition Device 1 Launch Ready to Launch Control launch Separation Booster Flight computer 2 burnout (accelerometer) (negative acceleration) Sustainer burn Stage 2 Flight computer 3 ignition delay elapses (timer) 4 Sustainer Apogee Deployment apogee/deployment altimeter (MAWD) 2a Booster apogee, Apogee Deployment main deployment altimeter (MAWD) 3a Booster touchdown Descent under Drogue - drogue deployment 6 Main ft Deployment deployment/descent reached altimeter (MAWD) 7 Sustainer touchdown Table 2: Flight events, including time and altitude of each event, condition that trigger an event and a device that executes the action associated with the event. 8. Removable shear pins will be used for both the main parachute compartment and the drogue parachute compartment. We shall use removable nylon shear pins of sufficient strength to prevent premature rocket separation. The size and number of shear pins will be fine tuned during test flights. 9. The vehicle, or any un-tethered sections, will have a descent rate under the main parachute(s) between 17ft/s and 22ft/s, inclusive. The estimated descent rate for both stages is 21ft/s. Vehicle Recovery Parachute name Parachute size [in] Descent rate [ft/] Ejection charge size [g] Booster Main Sustainer Drogue Main Table 3: The parachute size, descent rate and estimated ejection charge size for the main and drogue parachutes -14-

15 10. The vehicle, or any un-tethered sections, will have a descent rate under the drogue parachute(s) between 50 and 100 ft/s, inclusive. Only the second stage of our vehicle will be use drogue controlled descent and the estimated descent rate under drogue for this stage is 89ft/s. The first stage is using single deployment (main parachute deployed at the stage apogee). 11. Each rocket will be capable of being prepared for flight at the launch site within 4 hours, from the time the waiver opens at the field until RSO inspections have been successfully completed. We shall use a vehicle preparation checklist so that we can prepare the rocket in the allotted time. 12. All vehicle and payload components will be designed to land within 2500 ft. of the pad with a 10 mile/hour wind. The table below indicates that even in the worst case scenario (wind speed at the NAR safety limit of 20mph) both stages will land within 2,500ft from the launch pad. Wind speed vs. Rocket drift Wind speed [mph] Booster drift [ft] Sustainer drift [ft] Table 4: Amount of rocket drift with varying wind speed. The table has been computed assuming sustainer apogee of 5,280ft, booster apogee of 1,650ft, sustainer main parachute deployment altitude of 700ft, booster main parachute deployment altitude of 1,650ft, drogue descent rate of 90ft/s and main parachute descent rates of 20ft/s. 13. After being fully armed for launch, the rocket will be capable of remaining on the pad for 1 hour before launching without losing the functionality of any vehicle or payload component. We shall construct the payload so that it can sit on the pad for at least one hour, and ensure that all batteries can run their circuits for at least one hour. Battery capacity testing will be conducted during payload construction and development; new batteries will be used for each flight. A preliminary review of the payload design has not identified any possible power bottleneck. 14. Rockets will be launched from a standard firing system (provided by the Range) that does not need additional circuitry or special ground support equipment to initiate the flight or complicate a normal 10-second countdown. We shall build the rocket using standard rail buttons and standard motor ignition systems to ensure that no additional equipment is needed for the launch. Staging, deployment and payload are controlled by autonomous onboard devices with lift-off detection capability (allowing most of the electronics to remain in the shallow sleep mode until the liftoff). -15-

16 15. The experiment will be designed to follow the scientific method. See section on independent and dependent variables for more information. 16. Each stage of the rocket will contain a telemetry device consisting from a GPS receiver and 900MHz transceiver (in transmitter mode) to aid in recovery. GPS satellite data will be received by the GPS receiver. The GPS receiver transfers the data over serial link to flight computer that will instruct 900MHz XBee transceiver to transmit the data. Another 900MHz XBee transceiver (located on the ground) will receive the GPS data broadcasted by the rocket and the GPS location will be entered into a handheld GPS device. The handheld GPS will guide the recovery to the landing site. Figure 5: Diagram of satellite-based telemetry system 17. The vehicle will be designed to reach the correct altitude using commercially available rocket motors with a total impulse of less than 4,000 Ns. The motors will contain commercially available ammonium perchlorate composite propellant (APCP) motors certified by the NAR or TRA. -16-

17 Motor Diameter [mm] Total Impulse [Ns] Burn Time [s] Booster Stability Margin [calibers] Thrust to weight ratio AT-J800T CTI-J1520V-MAX AT-J1999N Sustainer AT-J1999N CTI-K2045V-MAX AT-K1100T Projected Apogee [ft] Table 5: Possible motor alternative both for the booster and sustainer stages. The preferred combination of the motors (Aerotech J800T (booster) and Aerotech J1999N (sustainer) is shown in bold-italic font). 18. There will be a full scale launch of the vehicle before the FRR teleconference. Any factors affecting stability, such as mass distribution, holes for cameras, etc. will be accounted for using payload simulators. See Project Timeline for additional details. Proposed Launch Schedule January Scale model test flight February Sustainer (upper stage) test flight March Two-stage test flight with payload April Launch at Huntsville, AL Table 6: Vehicle Schedule 19. None of the following will be used: flash bulbs, forward canards, forward-firing motors, rear ejection, motors with titanium sponges. Flashbulbs: NO. The rocket will eject parachutes using commercially available low-current e-matches. Forward canard fins: NO (cf. Vehicle Design). Forward-firing motors: NO. Rear-ejection parachute designs: NO (standard e-bay coupling arrangement will be used for parachute deployment). -17-

18 Motors which expel titanium sponges: NO. None of our proposed motors contain titanium sponges. 20. A final launch and safety checklist will be included in the FRR and used during the safety inspection and on launch day. The checklist will be continuously updated as the project progresses. Test flights will be used to fine tuned and test the checklist. 21. Students will do all of the work on the project except for handling motors and black powder charges. -18-

19 Major Milestones Schedule Major Milestones November Supplementary Presentation December Preliminary Design Review Presentations 11 Begin work on scale model January Scale Model Completed 5 Purchase parts and supplies for full scale vehicle 15 Scale model test flight 24 Critical Design Review report and CDR presentation slides due February CDR Presentation practice 2-8 Critical Design Review presentations (tentative) 6 Payload design finalized, payload construction starts 13 Full scale vehicle completed 20 Sustainer (upper stage) test flight March Two stage test flight, payload complete 21 Flight Readiness Review report and FRR presentation slides due 22 Payload test flight FRR presentations (tentative) April Rocket Ready for Launch in Huntsville 13 Travel to Huntsville Rocket Fair/hardware and safety check 16 Launch day 17 Return Home May Post-Launch Assessment Review (PLAR) due Table 7: Timeline of important events -19-

20 Design Review at System Level and Required Subsystems Propulsion System Booster Motor Aerotech J800T is suggested as the first choice for the booster. It will provide sufficient thrust for the liftoff of the entire vehicle (thrust/weight ratio is 6.3) and will burn out at around 250ft after accelerating the rocket to about 175mph. The booster is expected to coast to 1600ft and single parachute will be used for recovery. Length Diameter Average Total Impulse Burn Time Motor [mm] [mm] Impulse [N] [Ns] [s] AT-J800T Table 8: The information for our primary booster motor Sustainer Motor After the separation from the booster, the J1999 motor will deliver the sustainer to the target altitude. The maximum estimated speed is 575mph and the motor will burn for 0.6s. Our past experiences using the Warp9 propellant indicate that sustainer ignition will not be a problem. Motor Length [mm] Diameter [mm] Average Impulse [N] Table 9: The information for our primary sustainer motor Total Impulse [Ns] Burn Time [s] AT-J1999N

21 Motor Alternatives Suitable alternative motors are listed in the table below. Motor Diameter [mm] Total Impulse [Ns] Burn Time [s] Booster Stability Margin [calibers] Thrust to weight ratio AT-J800T CTI-J1520V-MAX AT-J1999N Sustainer AT-J1999N CTI-K2045V-MAX AT-K1100T Projected Apogee [ft] Table 10: Possible motor alternative both for the booster and sustainer stages. The preferred combination of the motors (Aerotech J800T (booster) and Aerotech J1999N (sustainer) is shown in bold-italic font). The motors will each be contained in a phenolic motor-mount tube, centered in the rocket body with three 0.50 plywood centering rings, and secured with a Lock N Load motor retention system. Structural System The structural system consists of 3 diameter fiberglass tubing. We are using 3 tubing because the rocket needs to be thin and have low mass so that we can achieve the high accelerations needed for our experiment. Two sets of three fins made of G10 fiberglass balsa composite will be attached with through the wall construction to the motor mounts in either stage. -21-

22 Entire Vehicle Figure 6: A two dimensional schematic of the entire rocket. Stability margin for the entire vehicle is 7.75 calibers. Vehicle Parameters Length [in] Mass [kg] Diameter [in] Motor Selection Stability Margin [calibers] Thrust to weight ratio AT-J800T Table 11: The rocket s dimensions, stability, and propulsion The figure below shows all compartments and section of our rocket. Each stage will contain one payload module. We will use standard dual deployment for the sustainer and single deployment for the booster. A B C E F H I J K M D K G L Figure 7: A three dimensional schematic of the entire rocket Letter Part Letter Part A Nosecone H Sustainer Motor Mount and Interstage Coupler B Sustainer Main Booster I Parachute Parachute C Sustainer E-Bay J Booster E-bay D Sustainer Drogue Parachute K Booster Payload E Sustainer Payload L Booster Fins F Telemetry/Staging Electronics M Booster Motor Mount G Sustainer Fins Table 12: Rocket sections and parts -22-

23 Sustainer Figure 8: A two dimensional schematic of the sustainer part of the rocket. Stability margin for the sustainer is 7.5 calibers. Sustainer Parameters Stability Thrust to Length Mass Diameter Motor Margin weight [in] [kg] [in] Selection [calibers] ratio AT-J Table 13: The dimensions of the sustainer, stability margin, and primary propulsion choice. Figure 9: A three dimensional schematic of the sustainer Deployment System The deployment system will be set up as follows: 1. Booster The booster deployment system will consist of two altimeters with two ejection charges for the booster parachute. Both altimeters fire their charge when they detect the booster s apogee releasing the parachute. Due to the low expected apogee of the booster we are using single deployment, only one parachute will be used. 2. Sustainer The separation of the rocket occurs shortly before the sustainers motor starts its burn (a separation charge will be used). The sustainer then continues to apogee. When apogee is reached two altimeters fire two charges and deploy the sustainer s drogue parachute (again two for redundancy). The sustainer then descends to an altitude of 500ft at which point the sustainer s main chute is deployed. -23-

24 2:3 Scale Model: Entire Vehicle Figure 10: A two dimensional schematic of the entire rocket. Stability margin for the entire scale model is 7.69 calibers. Scale Model Vehicle Parameters Length [in] Mass [kg] Diameter [in] Motor Selection Stability Margin [calibers] Thrust to weight ratio AT-H669N Table 14: The scale model s dimensions, stability, and propulsion The figure below shows all compartments and section of our scale model design. Each stage will contain one mock payload module. We will use standard single deployment for both the sustainer and booster. A B C E F H I J K M K G L Figure 11: A three dimensional schematic of the entire scale model Letter Part Letter Part A Nosecone H Sustainer Motor Mount and Interstage Coupler B Sustainer Main Booster I Parachute Parachute C Sustainer E-Bay J Booster E-bay E Sustainer Mock Payload K Booster Mock Payload F Telemetry/Staging Booster L Electronics Fins G Sustainer Fins M Booster Motor Mount Table 15: Scale model sections and parts -24-

25 Scale Model Sustainer Figure 12: A two dimensional schematic of the sustainer part of the scale model. Stability margin for the sustainer is 6.1 calibers. Scale Model Sustainer Parameters Stability Thrust to Length Mass Diameter Motor Margin weight [in] [kg] [in] Selection [calibers] ratio AT-H220T Table 16: The dimensions of the sustainer, stability margin, and primary propulsion choice. Figure 13: A three-dimensional schematic of the scale model sustainer Scale Model Deployment System The deployment system for the scale model rocket will be set up as follows: 1. Booster The booster deployment system will consist of two altimeters with two ejection charges for the booster main parachute. Both altimeters fire their charge when they detect the booster s apogee releasing the parachute. Due to the low expected apogee of the booster we are using single deployment, only one parachute will be used. 2. Sustainer The separation of the scale model rocket occurs shortly before the sustainer s motor starts its burn (a separation charge will be used). The sustainer then continues to apogee. When apogee is reached, two altimeters fire two charges and deploy the sustainer s main parachute (again two for redundancy). The sustainer then descends to an altitude of 500ft at which point the sustainer s main chute is deployed. -25-

26 Madison West High School Senior Team SLI 2011 PDR Flight Sequence The following figure and table show the flight sequence necessary to carry out our experiment. Figure 14: Mission profile chart (flight sequence). -26-

27 Event Time [s] Altitude Triggering Triggering [ft] Condition Device 1 Launch Ready to Launch Control launch Separation Booster Flight computer 2 burnout (accelerometer) (negative acceleration) Sustainer burn Stage 2 Flight computer 3 ignition delay elapses (timer) 4 Sustainer Apogee Deployment apogee/deployment altimeter (MAWD) 2a Booster apogee, Apogee Deployment main deployment altimeter (MAWD) 3a Booster touchdown Descent under Drogue - drogue deployment 6 Main ft Deployment deployment/descent reached altimeter (MAWD) 7 Sustainer touchdown Table 17: Mission profile events. -27-

28 Performance Characteristics for the System Verification Plan and Status Verification Tests V 1 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. 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: Telemetry and Beacons C11: Shock cords and anchors C12: Rocket stability C13: Second stage separation and ignition electronics/charges -28-

29 Matrix Legend XXX: Planned Tests XXX: Finished Tests V 1 V 2 V 3 V 4 V 5 V 6 V 7 V 8 V 9 V 10 C 1 P P C 2 P P C 3 P P C 4 C 5 C 6 C 7 C 8 P C 9 C 10 C 11 P P C 12 C 13 Table 18: Verification matrix for the vehicle Our verification plan is 0% complete; however, all of the necessary tests will be completed before our departure to Huntsville. -29-

30 Rocket/Payload Risks Risks Consequences Mitigation Unstable rocket Errant flight Rocket stability will be verified by computer and scale model flight. Improper motor mounting Weak rocket structure Propellant malfunction Damage or destruction of rocket. Rocket structural failure Engine explosion Engine system will be integrated into the rocket under proper supervision and used in the accordance with the manufacturer's recommendations. Rocket will be constructed with durable products to minimize risk. All members will follow NAR Safety Code for High Powered Rocketry, especially the safe distance requirement. Attention of all launch participants will be required. Mentors will assemble the motors in accordance with manufacturer's instructions. Parachute Parachute failure Parachute packaging will be double checked by team members. Deployment of parachutes will be verified during static testing. Payload Launch rail failure Separation failure Ejection falsely triggered Recovery failure Transportation damage Payload failure/malfunction Errant flight Parachutes fail to deploy Unexpected or premature ignition/personal injury/property damage Rocket is lost Possible aberrations in launch, flight and recovery. Team members will double-check all possible failure points on payload. NAR Safety code will be observed to protect all member and spectators. Launch rail will be inspected prior each launch. Separation joints will be properly lubricated and inspected before launch. All other joints will be fastened securely. Proper arming and disarming procedures will be followed. External switches will control all rocket electronics. The rocket will be equipped with radio and sonic tracking beacons. Rocket will be properly packaged for transportation and inspected carefully prior to launch Table 19: Risks associated with the rocket launch -30-

31 Specific Two Stage Vehicle Risks Risks Consequences Mitigation Stages fail to separate Second stage motor fails to ignite Second stage motor fires late Motor failure (chuff or CATO) Stage 2 motor burns while still attached to booster No second stage separation, rocket too heavy for safe descent rate Horizontal second stage flight Second stage mistakenly detects launch and ignites Make sure coupler fit is exact, and use a previously tested method for use in twostage rockets of this size. The size of separation charge will be verified in static testing. Recommended staging igniters will be used and the staging electronics will thoroughly tested before each flight. Recovery of all stages is triggered by altimeters and all recovery devices will deploy even if the second stage fails to ignite. Members will check that the timer is accurately set, a reliable igniter will be used, and we will use new batteries for each flight. We will use reliable motors and electronics. The timers require 2g+ acceleration for 0.5s before they trigger the timer countdown. Table 20: Risks associated with a two stage rocket launch Scheduling and Facilities Risks Risks Consequences Mitigation Workshop space unavailable Unable to complete construction of rocket and/or We will ensure the availability of our workshop space for the times that we need it. We will also work at team members Design facilities unavailable Team members unavailable payload Unable to complete project Unable to complete project homes if necessary. We will ensure the availability of our design facilities and work at team members homes if needed. We will plan meetings in advance and insure that enough team members will be present to allow sufficient progress. Table 21: Risks associated with scheduling and facilities Integrity of Design We have chosen standard high power rocketry materials namely G-10 fiberglass balsa sandwich for the fins, half-inch plywood for the bulkheads, fiberglass tubing for the body, stainless steel hardware to ensure structural integrity of the vehicle during flight and landing. The standard trapezoidal shape and proper size of our fins ensures the stable flight of our vehicle and reduces the risk of fin flutter during ascent. We will employ an Aeropack motor retention system to ensure that the motor does not dislodge during flight. Our use of West Systems Epoxy on the full scale vehicle will ensure the robustness of load-bearing structural sections of the rocket; specifically, attachment points of the fins to the body tubes, connections of couplers to body tubes, and fixture points of permanent bulkheads and centering rings within body tubes. -31-

32 Recovery Subsystem Our rocket will deploy a total of three parachutes. We will utilize the standard deployment scheme with redundant charges and ejection triggers to ensure the ejection and will determine and verify the sizes of parachutes and ejection charges during static tests. Two parachutes are housed in the sustainer. The sustainer drogue chute will be deployed at sustainer s apogee, slowing and stabilizing the rockets descent. The sustainer s main chute will be deployed at 700ft, slowing the rocket to a safe descent rate. The other parachute is housed in the booster. Vehicle Recovery Parachute name Parachute size [in] Descent rate [ft/] Ejection charge size [g] Booster Main Sustainer Drogue Main Table 22: Vehicle Recovery The ejection charge sizes were calculated with the formula where Wp=dP*V/(R*T) Wp - ejection charge weight in pounds. dp - ejection charge pressure, 15psi. V - free volume in cubic inches. R- combustion gas constant, ft- FFFF black powder. T combustion gas temperature, 3307 degrees R -32-

33 Payload Integration Payload Bay Payload Bay Figure 15: Payload Integration The payload team has been provided four bays of adequate size for the payload capsules. The payload has a limitation of 28 inches and 2 kilograms each for the sustainer and booster. Payload integration is described in detail in the Payload section. Launch Operation Procedures Launch System and Platform Our launch system will consist of a standard 12 foot rail, and the ignition will be standard electronic ignition system of the type supplied by the field operations personnel in Huntsville. Final Assembly and Launch Procedures The rocket will be transported to Huntsville separated into multiple pieces in order to fit the transpiration methods. Once in Huntsville, minimal assembly will be required to get the rocket into a flyable configuration. The payload will be transported outside of the rocket in an environment where the temperature and pressure between the control and flight modules can be controlled. Once at the launch field, we will perform the very final steps which would not have been safe and/or scientifically rigorous to perform beforehand (such as attachment of ejection charges and insertion of payload environmental chambers). We will ensure that our field prep time is as low as possible by performing as much of the pre-flight prep as is safely and scientifically possible before the rockets transportation to Huntsville. In addition to preparing the rocket ahead of time, we will also develop a rigorous payload, vehicle, and payload/vehicle integration checklist. This will allow us to develop a plan for the launch preparation procedures as well as check our work to prevent costly mistakes. After the rocket is launched, we will recover it using radio telemetry to pinpoint its location. We have designed a system which would use GPS and a radio telemetry chip to allow us to receive the digital signal and translate it into a map position. This would greatly cut down on the amount of time spent searching for the rocket, both in Huntsville and in the thick forests and swamps of the Bong State Recreation Area. -33-

34 Vehicle Checklist Vehicle/Paylaod Integration Checklist Launch Operations Checklsit Telemety Recovery Paylaod Checklist Figure 16: Launch procedure Safety and Environment (Vehicle) Safety Officer Our Safety officer is Yifan Li. Risks and Mitigations Physical Risks Risks Consequences Mitigation Saws, knives, Dremel tools, band saws Laceration All members will follow safety procedures and use protective devices to minimize risk Sandpaper, fiberglass Abrasion All members will follow safety procedures and use protective devices to minimize risk Drill press Puncture wound All members will follow safety procedures and use protective devices to minimize risk Soldering iron Burns All members will follow safety procedures to minimize risk Computer, printer Workshop risks Electric shock Personal injury, material damage All members will follow safety procedures to minimize risk All work in the workshop will be supervised by one or more adults. The working area will be well lit and strict discipline will be required Table 23: Risks that would cause physical harm to an individual -34-

35 Rocket/Payload Risks Risks Consequences Mitigation Unstable rocket Errant flight Rocket stability will be verified by computer and scale model flight. Improper motor mounting Weak rocket structure Propellant malfunction Damage or destruction of rocket. Rocket structural failure Engine explosion Engine system will be integrated into the rocket under proper supervision and used in the accordance with the manufactures recommendations. Rocket will be constructed with durable products to minimize risk. All members will follow NAR Safety Code for High Powered Rocketry, especially the safe distance requirement. Attention of all launch participants will be required. Mentors will assemble the motors in accordance with manufacturer's instructions. Parachute Parachute failure Parachute Packaging will be double checked by team members. Deployment of parachutes will be verified during static testing. Payload Launch rail failure Separation failure Ejection falsely triggered Recovery failure Transportation damage Payload failure/malfunction Errant flight Parachutes fail to deploy Unexpected or premature ignition/personal injury/property damage Rocket is lost Possible aberrations in launch, flight and recovery. Team members will double-check all possible failure points on payload. NAR Safety code will be observed to protect all member and spectators. Launch rail will be inspected prior each launch. Separation joints will be properly lubricated and inspected before launch. All other joints will be fastened securely. Proper arming and disarming procedures will be followed. External switches will control all rocket electronics. The rocket will be equipped with radio and sonic tracking beacons. Rocket will be properly packaged for transportation and inspected carefully prior to launch Table 24: Risks associated with the rocket launch -35-

36 Specific Two Stage Vehicle Risks Risks Consequences Mitigation Stages fail to separate Second stage motor fails to ignite Second stage motor fires late Motor failure (chaff or CATO) Stage 2 motor burns while still attached to booster No second stage separation, rocket too heavy for safe descent rate Horizontal second stage flight Second stage mistakenly detects launch and ignites Make sure coupler fit is exact, and use a previously tested method for use in twostage rockets of this size. The size of separation charge will be verified in static testing. Recommended staging igniters will be used and the staging electronics will thoroughly tested before each flight. Recovery of all stages is triggered by altimeters and all recovery devices will deploy even if the second stage fails to ignite. Our members will check that the timer is accurately set, a reliable igniter will be used, and we will supply new batteries for each flight. We will use reliable motors and electronics. The timers require 2g+ acceleration for 0.5s before they trigger the timer countdown. Table 25: Risks associated with a two stage rocket launch Toxicity Risks Risks Consequences Mitigation Epoxy, enamel paints, primer, Toxic fumes superglue substances Superglue, epoxy, enamel paints, primer Toxic substance consumption Area will be well ventilated and there will be minimal use of possibly toxic-fume emitting All members will follow safety procedures to minimize risk. Emergency procedure will be followed in case of accidental digestion. Table 26: Risks that would cause toxic harm to an individual Environmental Concerns With any activity such as rocketry, one can cause damage to the environment. Fumes emitted from the engine of the rocket during the launch can possibly cause air pollution; rockets that aren t recovered could cause physical harm to animals, and any nonbiodegradable material will remain for years. To try to minimize the potential environmental hazards associated with rocketry, we will strictly comply with all state and federal environmental regulations. We will keep track of everything we use to launch our rockets and the rockets themselves to ensure that all parts are recovered. We will use Nomex parachute protection to avoid littering the launch area with flame retardant wadding. -36-

37 Payload Criteria Selection, Design, and Verification of Payload Experiment Design at System Level Designed as independent units, each Environmental Chamber studies the effect of hypergravity on Fargesia Fungosa seedlings based on its assigned orientation. For redundancy, we have included four chambers in both the booster and the sustainer, two of each orientation. Other then the Agar Containment Unit in the Horizontally Positioned Bamboo Chamber, each chamber design consists of the same systems: a Mechanical System, Biological System, Data Process and Storage System, Monitoring Components System. Robust and weight-efficient, the Mechanical System provides adequate protection to the vital components inside, while adhering to the weight constraint imposed by the vehicle team. Materials were chosen because of availability and low costs; furthermore, the clear acrylic tubing will let us view the interior of the chamber at all time. The bamboo species a Biological System component was a difficult choice. Of the problems we encountered while choosing the species, finding an available plant store caused the most distress. It was difficult enough to find a small plant type that would fit in our rocket, but finding a store that sold it in our area was even harder. We eventually chose Fargesia Fungosa because of the price, and ordered it from a German plant store online. Both the Data Process and Storage System and the Monitoring Components System were chosen based on previous experience with experiments that require electronics. To simplify our subsystem organizations, we divided the electronic elements into these basic categories. Payload Systems Our payload consists of three major systems: the Mechanical System, The Biological System, Data Processing and Storage System, Monitoring Components System. Mechanical System The Mechanical System is the containment system for our payload. This system helps control the experiment. Each Environmental Chamber includes a Vessel, which holds the Biological System. At the end of each Vessel is an Inter-Payload Bulkhead. The Vessel will fit between the bulkheads and there will be tie-rods running through the bulkheads to fix the vessel in place. -37-

38 Inter-Payload Bulkhead Vessel Figure 17: Mechanical System of our Environmental Chamber Vessel Subsystem Inter-Payload Bulkheads Function A 2.50 inch acrylic tube, the vessel will contain the Biological System of our payload. These bulkheads will be the 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. Table 27: Subsystems of the Mechanical System Accuracy/Precision Requirements N/A We will print these bulkheads using 3-D printers to ensure that all components will attach correctly. -38-

39 Biological System The Biological System of our payload includes Agar Gel, Fargesia Fungosa (Bamboo Seedling), Agar Containment Unit. The Agar Containment Unit is used exclusively for the horizontally growing bamboo. The agar will contain all the necessary nutrients and be of a sufficient density to go through the gravitational forces generated during flight. The bamboo will be grown to a specific age before being flown. Agar Containment Unit Bamboo Agar Gel Figure 18: Biological System of the Environmental Chamber -39-

40 Agar Gel Subsystem Fargesia Fungosa (Bamboo Seedling) Agar Containment Unit Function We will grow our Bamboo seedlings in the agar. The agar will provide nutrients for the bamboo during the entire growth cycle. Bamboo seedlings will be planted in the Agar gel. Once they are a week old, the bamboo seedlings will be flown in our vehicle. This will be used specifically for the horizontally growing bamboo. This vessel will contain the Agar Gel and bamboo. Accuracy/Precision Requirements Consistency of the Agar Gel in terms of nutrients and density. Bamboo seedlings will be grown to the correct age. N/A Data Processing and Storage System Table 28: Subsystems of the Biological System The Data Processing and Storage System involves storage of data collected from the satellite boards as well as the various miscellaneous items required for the successful functioning of electronics. Subsystem Function Accuracy/Precision EEPROM Programs the CPU N/A Cable and Data Transfer Transfer data from satellite board to central board N/A Power Source Powers the electronics N/A G-Switch Start collecting data after liftoff N/A Power Convertor Divide power into 5.00V, and ground N/A ADC (Analog to Digital Converts the analog to a 16bit, 3kSps Convertor) digital signal CPU (Central Processing Unit) Initiates the reaction, collects the temperature profiles and controls the fans A Parallax Propeller Chip, 8 cores, 80MHz clock, 32 kb RAM Memory Stores Data Atmel AT26/25 flash memory, 2MB Table 29: Subsystems of the Data Processing and Storage System -40-

41 Figure 19: Left: The central flight computer includes the G-Switch, EEProm, ADC, Power Convertor, Buzzer, Memory and connectors. Right: The layout of central flight computer and satellite payload controllers. Monitoring Components System The Monitoring Components system records data from the various Environmental Chambers. It collects temperature, humidity and light sensor data. It also provides power for the light source for constant lighting in the environmental chambers. Subsystem Function Accuracy/Precision Cable and Data Transfer Transfer data from satellite board to central board N/A Starts collecting data after Thermistor measures to Temperature Sensor liftoff 0.1 of a degree, measures 1 time a Humidity Sensor Light Sensor Light Source Starts collecting data after liftoff Detects the light intensity in payload Keeps constant lighting in payload Table 30: Subsystems of the Monitoring Components System second Humidity sensor measures to 0.1 percent, time a second N/A N/A -41-

42 Performance Characteristics System Mechanical System Biological System Data Processing and Storage System Subsystems 1. Vessel 2. Inter-Payload Bulkhead 1. Agar Gel 2. Fargesia Fungosa (Bamboo Seedlings) 3. Agar Containment Unit 1. Master Flight Computer Storage Subsystem 2. Cable and Data Transfer 3. Power Source Performance Characteristics 1. Adequately contains Biological System 2. Reliably isolates and separates each chamber 3. Reliably holds Electronics in place 4. Manages experiment variables 1. Supports seedling position 2. Must withstand gravitational forces generated by rocket flight 3. Reliably provide equal nutrition to all bamboo 4. Keeps Agar still throughout entire trajectory 1. Stores data reliably, low data corruption rate 2. Transfers data correctly, high signal to noise ratio Monitoring Components System 1. Temperature Sensor 2. Humidity Sensor 3. Light Sensor 4. Light Source 5. Cable and Data Transfer Table 31: Performance Characteristics of each Systems and subsystems Reliably monitors temperature inside chambers 2. Reliably monitors humidity inside chambers 3. Reliably monitors light inside chambers 4. Provides consistent and regular lighting 5. Transfers data correctly, high signal to noise ratio

43 Verification Matrix The components and tests for the verification matrix are listed below. Verification Test 1. Drop Test: Drop components to ensure that they will not break in flight or during landing. Drop height will be chosen so that it simulates a rocket landing. 2. Connection and Basic Functionality Test: Ensure that all electronic components, devices and batteries are connected firmly and will not loosen in flight. When possible verify that powered up component functions correctly. 3. Pressure Chamber Test: We will place the altimeter in a chamber to make sure the altimeter registers the correct pressure 4. Scale Model Flight: When possible, include component in scale model flight to verify that the component can function during flight. 5. Temperature and Humidity Sensor Test: Place sensors in a known setting in terms of temperature and humidity level to verify that they register the correct values. 6. Durability Test: Verify that the various components will not detach during flight. 7. Battery Capacity Test: Verify that our batteries will supply enough power for our electronics to function for a sufficient time (at least one hour). 8. Final Test: Test the complete subsystem for its function. P=Planed F=Finished Vessel P P P P Inter-Payload Bulkhead P P P P P Agar Gel P P P P P Fargesia Fungosa (Bamboo Seedlings) P P P P P P Agar Containment Unit P P P P Master Flight Computer Storage Subsystem P P P P P P P Cable and Data Transfer P P P P P P Power Source P P P P P P Temperature Sensor P P P P P P Humidity Sensor P P P P P P Light Sensor P P P P P P Light Source P P P P P Table 32: Verification Matrix of the Payload -43-

44 Payload Preliminary Integration Figure 20: Integration of the payload into the vehicle The payload portion of our rocket integrates easily with the vehicle. There will be payload components in both the sustainer and booster sections of our rocket. Payload components will stay in place for the duration of rocket flight and are independent of vehicle subsystems. The payload meets size and weight constraints imposed by the vehicle, and will be able to withstand the stresses of rocket flight. We are looking for a design that will allow for easy installation and removal of the payload. To investigate the effects of hypergravity on Fargesia Fungosa, we designed chambers that will hold the bamboo shoots and its aiding components. We designed similar chambers to hold the horizontal and vertical bamboo specimens. 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. Precision of Instrumentation, Repeatability of Measurement and Recovery System Please refer back to the Payload Subsystem section for the precision of instrumentation. Our payload is designed for easy repetition of the experiment. Temperature sensors and humidity sensors will be mounted on the satellite boards in each of the eight environmental chambers. The payload will not eject from the rocket and therefore will not have its own recovery system. -44-

45 Payload Concept Features and Definition Creativity and Originality Our payload this year is very complex and involved, primarily in the scientific goals of the project. In our previous year, our post-flight analysis was relatively simple; the analysis was completed using off-the-shelf equipment that required reliantly little expertise to operate. This year we have conceived of a complicated payload specimen analysis project to determine with a much greater degree of certainty what the effect of the acceleration is on the payload specimens. We also have designed an intricate and modular payload capsule design that will allow us to standardize the atmospheric conditions across the control, first stage, and second stage flight capsule payload modules. This control will allow us to ensure better scientific results and will also give us firm footing for future experiments that require environmental chambers (this modular payload design could be adapted to many different payloads). The modularity of the payload will also allow us to easily replace a payload module in the event of breakage during transport, contamination, etc. Uniqueness or Significance We have increased our complexity and scientific value from our previous experiments on the effect of hypergravity on various plants mainly by increasing the sheer amount of scientific analysis that is to be done. Previous experiments have only tested the effect of gravity on a single variable, such as growth or marked gene expression. We instead will determine the effect of gravity on many variables, such as growth, robustness, crosssection analysis (radial and axial), density, metabolism differences, gene expression, hemocellulose concentration differences, lignin concentrations, and rhizome testing. In addition to testing many different variables, we will also be using a different kind of plant. Bamboo is a much different plant, and it presents its own unique set of challenges and characteristics. -45-

46 Suitable Level of Challenge Our payload this year is very complex and involved, primarily in the scientific goals of the project. In our previous year, our post-flight analysis was relatively simple; the analysis was completed using off-the-shelf equipment that required relatively little expertise to operate. This year we have conceived a complicated payload specimen analysis project to determine with a much greater degree of certainty what the effect of the acceleration is on the payload specimens. We also have designed an intricate and modular payload capsule design that will allow us to standardize the environmental conditions across the control, first stage, and second stage flight capsule payload modules. This control will allow us to ensure better scientific results and will also give us firm footing for future experiments that require environmental chambers (this modular payload design could be adapted to many different payloads). The modularity of the payload will also allow us to easily replace a payload module in the event of breakage during transport, contamination, etc. We have increased our complexity and scientific value from our previous experiments on the effect of hyper-gravity on various plants mainly by increasing the sheer amount of scientific analysis that is to be done. Previous experiments have only tested the effect of gravity on a single variable, such as growth or marked gene expression. We instead will determine the effect of gravity on many variables, such as growth, robustness, cross-section analysis (radial and axial), density, metabolism differences, gene expression, hemocellulose concentration differences, lignin concentrations, and rhizome testing. In addition to testing many different variables, we will also be using a different kind of plant. Bamboo is a much different plant, and it presents its own unique set of challenges and characteristics. The rocket vehicle itself is designed to deliver maximum achievable acceleration without exceeding the altitude target of one mile. The preliminary estimates indicate that the sustainer of our vehicle will experience 30g, which is significantly more than in our other projects. We have never undertook a two stage projects with these parameters. Additionally, in order to satisfy performance target #16 (GPS location broadcast) we will be adding telemetry to our vehicle and payload. While we posses significant expertise in electronic design, wireless communications will be a fresh addition to our projects. We will strive to develop not just a GPS location broadcaster but a fully featured telemetry system that will broadcast the payload as well. -46-

47 Science Value Payload Objectives We will be investigating the effect of hypergravity on the growth and healing of bamboo shoots. Hypergravity research has been done on various plants in laboratories, but because they are done within centrifuges rapid acceleration and deceleration cannot be easily produced. Although our rocket will not reach extremely high acceleration values, it will go through a rapid acceleration which cannot be obtained in a centrifuge. Therefore, we will concentrate on the effect of rapid acceleration (jerk) on bamboo. We are currently experimenting with Fargesia Furgosa to learn about various properties of this species to establish a control. Payload Success Criteria 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 -47-

48 Describe Experimental Logic, Approach and Method of Investigation After a successful flight, we will take our bamboo payload to a laboratory for analysis. Figure 21: Sampling of bamboo for postflight analysis. The figure above shows how the bamboo will be sampled for postflight analysis. For simplicity the procedure is shown with 4 bamboo plants and over 4 days. Day 1: collect sample from plant #1 (leftmost), measure cross section changes, bamboo strength characteristics and then use the plant for chemical analysis. Note that the observations are invasive and the analyzed bamboo section will be compromised by sampling and measurement. For this reason each bamboo plant that undergoes analysis cannot be included in later observations. 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: same as Day #2, but three sections are sampled (Day #1 growth, Day #2 growth, Day #3 growth). -48-

49 The above outlined sampling procedure will allow us to observe entire history of developments in bamboo plant. However, it also requires large number of samplings and thus presents a major challenge. We plan to employ the entire team in the postflight analysis and divide the work among four groups, each group having two members. The groups will rotate in the lab duties. Correlations G = f (A, T) R = f (A, T) C R = f (A, T) C A = f (A, T) D = f (A, T) GE = f (A, T) H = f (A, T) L = f (A, T) Z = f (A, T) Bamboo Growth in relation to Acceleration Bamboo Robustness in relation to Acceleration Cross Section Changes (Radial) in relation to Acceleration Cross Section Changes (Axial) in relation to Acceleration Resulting Density of Bamboo in relation to Acceleration Gene Expression in relation to Acceleration Hemicellulose Concentration in relation to Acceleration Lignin Concentration in relation to Acceleration Rhizome Testings in relation to Acceleration Test and Measurement, Variables and Controls Test Specific Measurements following abovementioned methods Bamboo Growth Length measurements on bamboo will be made every day for three weeks Bamboo Robustness Break strength meter will measure robustness Radial Cross Section changes We will quantify details from microscope analysis of bamboo cross sections (radial) Axial Cross Section changes We will quantify details from microscope analysis of bamboo cross sections (axial) Density of bamboo Weight and volume measurements taken every day for Gene Expression Use of Polymerase Chain Reaction (PCR) available to us from UW Madison Hemicellulose Concentrations High Performance Liquid Chromatography (HPLC) analysis Lignin Concentrations Stress testing Rhizome Testing Length measurements on bamboo roots Table 33: Test and Measurement, Variables and Controls -49-

50 Independent Variables A T Acceleration Age of plant Dependent Variables G R C R and C A D GE H L Z Bamboo growth Bamboo robustness Changes in cross section (radial and axial) Resulting plant density Gene expression Hemicellulose concentration Lignin concentrations Rhizome testing Constants Light Exposure Bamboo Specimen Growing Conditions Testing Methods Bamboo Orientation in Payload Chambers Show Relevance of Expected Data and Accuracy/Error Analysis The correlations that can be made from our experiment can help us better understand the healing of bamboo plants from hypergravity-induced damage. The change in cell structure as a result in the healing process may cause increased strength in the bamboo. As an alternative and green building material, knowledge of how the structural strength of bamboo can be increased is relevant. All of the seedlings will be planted and grown in environmentally controlled chambers. The bamboo species, growing conditions, testing methods, and acceleration on the bamboo will remain constant throughout the payload. To ensure the accuracy of our experiment, there will be two redundant environmental chambers for each orientation and acceleration. There will also be control groups that will remain grounded and will be tested with the same procedures as the bamboo that was flown. Preliminary Experiment Process Procedure In the following weeks, we will prepare our lab procedures for post-flight labs. We will develop specific testing methods and gather necessary tools for post-flight analysis. Preliminary testing on sample bamboo will be completed to ensure mistakes on postflight bamboo will not occur. Finally, we will seek experts in botanists to discuss our procedure and to make improvements to it. -50-

51 Safety and Environment Safety Officer: Yifan Li NAR Safety Requirements a. Certification and Operating Clearances: Mr. Lillesand holds a Level 3 HPR certification. Dr. Pinkas has a Level 1 HPR certification and plans on having a Level 2 HPR certification by the end of February Mr. Havlena holds a level 1 HPR certification. He plans to complete his Level 2 by April 2011 and is our back-up launch supervisor. Mr. Lillesand has Low Explosives User Permit (LEUP). If necessary, the team can store propellant with Mr. Goebel, who owns a BATFE approved magazine for storage of solid motor grains containing over 62.5 grams of propellant. Mr. Lillesand is the designated individual rocket owner for liability purposes and he will accompany the team to Huntsville. Upon their successful L2 certification, Mr. Havlena and Dr. Pinkas will become a backup mentors for this role. All HPR flights will be conducted only at launches covered by an HPR waiver (mostly the WOOSH/NAR Section #558 10,000ft waiver for Richard Bong Recreation Area launch site). All LMR flights will be conducted only at the launches with the FAA notification phoned in at least 24 hours prior to the launch. NAR and NFPA Safety Codes for model rockets and high power rockets will be observed at all launches. Mentors will be present at all launches to supervise the proceedings. b. Motors: We will purchase and use in our vehicle only NAR-certified rocket motors and will do so through our NAR mentors. Mentors will handle all motors and ejection charges. c. Construction of Rocket: In the construction of our vehicle, we will use only proven, reliable materials made by well established manufacturers, under the supervision of our NAR mentors. We will comply with all NAR standards regarding the materials and construction methods. Reliable, verified methods of recovery will be exercised during the retrieval of our vehicle. Motors will be used that fall within the NAR HPR Level 2 power limits as well as the restrictions outlined by the SLI program. Lightweight materials such as fiberglass tubing and carbon fiber will be used in the construction of the rocket to ensure that the vehicle is under the engine s maximum liftoff weight. The computer program RockSim will be utilized to help design and pre-test the stability of our rocket so that no unexpected and potentially dangerous problems with the vehicle occur. Scale model of the rocket will be built and flown to prove the rocket stability. d. Payload: As our payload does not contain hazardous materials, it does not present danger to the environment. However, our NAR mentors will check the payload prior to launch in order to verify that there will be no problems. e. Launch Conditions: Test launches will be performed at Richard I. Bong Recreation -51-

52 Area with our mentors present to oversee all proceedings. All launches will be carried out in accordance with FAA, NFPA and NAR safety regulations regarding model and HPR rocket safety, launch angles, and weather conditions. Caution will be exercised by all team members when recovering the vehicle components after flight. No rocket will be launched under conditions of limited visibility, low cloud cover, winds over 20mph or increased fire hazards (drought). II. Hazardous Materials All hazardous materials will be purchased, handled, used, and stored by our NAR mentors. The use of hazardous chemicals in the construction of the rocket, such as epoxy resin, will be carefully supervised by our NAR mentors. When handling such materials, we will make sure to carefully scrutinize and use all MSDS sheets and necessary protection (gloves, goggles, proper ventilation etc.). All MSDS sheets and federal/state/local regulation applicable to our project are available online at III. Compliance with Laws and Environmental Regulations All team members and mentors will conduct themselves responsibly and construct the vehicle and payload with regard to all applicable laws and environmental regulations. We will make sure to minimize the effects of the launch process on the environment. All recoverable waste will be disposed properly. We will spare no efforts when recovering the parts of the rocket that drifted away. Properly inspected, filled and primed fire extinguishers will be on hand at the launch site. Cognizance of federal, state, and local laws regarding unmanned rocket launches and motor handling The team is cognizant and will abide with the following federal, state and local laws regarding unmanned rocket launches and motor handling: Use of airspace: Federal Aviation Regulations 14 CFR, Subchapter F, Part 101, Subpart C Handling and use of low explosives: Code of Federal Regulation Part 55 Fire Prevention: NFPA1127 Code for High Power Rocket Motors All of the publications mentioned above are available to the team members and mentors via links to the online versions of the documents

53 WRITTEN STATEMENT OF SAFETY REGULATIONS COMPLIANCE All team members understand and will abide by the following safety regulations: a. Range safety inspections of each rocket before it is flown. Each team shall comply with the determination of the safety inspection. b. The Range Safety Officer has the final say on all rocket safety issues. Therefore, the Range Safety Officer has the right to deny the launch of any rocket for safety reasons. c. Any team that does not comply with the safety requirements will not be allowed to launch their rocket. IV. Education, Safety Briefings and Supervision Mentors and experienced rocketry team members will take time to teach new members the basics of rocket safety. All team members will be taught about the hazards of rocketry and how to respond to them; for example, fires, errant trajectories, and environmental hazards. Students will attend mandatory meetings and pay attention to pertinent s prior participation in any of our launches to ensure their safety. A mandatory safety briefing will be held prior each launch. During the launch, adult supervisors will make sure the launch area is clear and that all students are observing the launch. Our NAR mentors will ensure that any electronics included in the vehicle are disarmed until all essential pre-launch preparations are finished. All hazardous and flammable materials, such as ejection charges and motors, will be assembled and installed by our NAR-certified mentor, complying with NAR regulations. Each launch will be announced and preceded by a countdown (in accordance with NAR safety codes). V. Procedures and Documentation In all working documents, all sections describing the use of dangerous chemicals will be highlighted. Proper working procedure for such substances will be consistently applied, such as using protective goggles and gloves while working with chemicals such as epoxy. MSDS sheets will be on hand at all times to refer to for safety and emergency procedures. All work done on the building of the vehicle will be closely supervised by adult mentors, who will make sure that students use proper protection and technique when handling dangerous materials and tools necessary for rocket construction. -53-

54 Activity Plan Budget Plan Project Budget Vehicle Tubing $ Fin Material $ PerfectFlite MAWD Altimeter (x4)* $ - PerfectFlite minitimer3 (x2)* $ - Parachutes, recovery gear* $ - Waltson/Tracking System $ - Miscellaneous supplies (tools, glues) $ Scale Model Tubing $ Fin Material $ Motors Scale Model Motors $ Preliminary Flight Motors $ Final Flight Motors $ - Payload Environmental Chambers (x 8) $ Bamboo $ Circuit Board and Sensors $ Total $ 1, Table 34: Budget for SLI Program (* - already in possession) -54-

55 Travel Budget Flight $400/Person * 10 People $ 4, Rooms $120/Room * 5 Rooms * 5 Nights $ 3, Car Rental $500 rental+ $228 gas $ Total $ 7, NASA Support ($1,200) $(1,200.00) Member cost $ 6, Cost per Team Member $ Table 35: Budget for the travel to Huntsville, AL Madison West Rocket Club has sufficient money earning opportunities to cover for possible discrepancies between the estimated budget and actual project expenses. Additionally, it is our policy to provide necessary economic help to all SLI students who cannot afford the travel expenses associated with the program. Every year we award several full expense travel scholarships both to our SLI and TARC students. The monetary amounts and the names of recipients are not disclosed. -55-

56 Timeline Timeline For SLI Project August Request for Proposal (RFP) goes out to all teams September One electronic version of the completed proposal due to NASA October Awards Granted. Schools notified of selection 13 PDR work begins 21 SLI teams teleconference November Web presence established for each team 19 PDR report and PDR presentation posted on team Website 20 Begin work on scale model 27 Acquire parts and supplies for scale model December PDR Presentation (tentative) 18 Scale Model Completed 19 Purchase parts and supplies for full scale vehicle 20 Payload Design Finalized and Bamboo Practice Experiments start 24-Jan 3 Winter break January Scale model test flight 24 CDR reports and presentations slides posted on team website February CDR Presentation (tentative) 5 Payload construction starts 13 Full scale vehicle completed 20 Sustainer (upper stage) test flight March Payload complete 12 Full Scale Test Flight with two stages 21 FRR reports and FRR presentation slides posted on team website FRR presentations (tentative) April /13 Rocket Ready for Launch in Huntsville/Travel to Huntsville 14/15 Rocket Fair/hardware and safety check 16/17 Launch weekend and Return Home May Post-Launch Assessment Review (PLAR) posted on team Website Table 36: Timeline for SLI Project -56-

57 Proposed Launch Schedule Proposed Launch Schedule January Scale model test flight February Sustainer (upper stage) test flight March Two-stage test flight with payload April /17 Launch at Huntsville, AL Table 37: Proposed Launch Schedule -57-

58 Educational Engagement Community Support After seven years of the club s existence, we are well known at various departments of the UW and many researchers are eager to work with us. During our six years of participation in SLI we have met with a number of people from various departments within the University of Wisconsin-Madison, including Professor McCammon from the department of Physics, Professor Eloranta from the department of Atmospheric Sciences, Professor Pawley from the department of Zoology, and Professors Anderson and Bonazza from the department of Mechanical Engineering. This year we have added Prof. Fernandez and Prof. Gilroy from the department of Botany, and Prof. Masson from the department of genetics.these contacts have been incredibly helpful in designing and refining our original experimental ideas and creating an experiment that will return meaningful data. DNASTAR Inc. has allowed us to use their building during the weekends. We hold our research meetings at DNASTAR conference rooms, which are equipped with state-ofart projection technology and also dry-erase whiteboards on which we can effectively diagram our ideas. Every year we raise funds by raking leaves during autumn in local neighborhoods. We find this is an excellent way to earn the support of the community and increase our visibility. Madison West Rocket Club has received a significant amount of publicity as a result of our first place ranking in the 2009 TARC contest. Many local newspapers and news channels carried the story. The Madison Metropolitan School District Media produced a short film detailing our achievements, which helped spread our accomplishments. The club also provides a steady stream of volunteers for public television and public radio fundraising drives. While this is not a direct display of our work or interests, it gives us the opportunity to provide public service in the name of our club. This year around 12 members of the club will be participating in Wisconsin Public Television pledge drives. In 2009 many club members gave back to the community by helping build a fence in the local soccer park where we also happen to launch our TARC practice flights in the winter. We are currently discussing other soccer park improvements with their management. -58-

59 Outreach Programs Madison West rocket club has recently cooperated with the Wisconsin Youth Organization to help Elm Lawn Elementary School students build and launch their A- Class rockets. Each club member worked one-on-one with an elementary student to help them build the rockets. A G-class rocket was launched by the club members to increase the "Awe" factor of the event. Figure 22: Rocket club member with elementary school student prepping for launch In addition, students were taught how to make Alka-Seltzer rockets using paper templates and film canisters. Figure 23: Elementary student coloring Alka-Seltzer rocket template -59-