Analysis of Pollen Distribution at Various Altitudes

Transcription

1 Analysis of Pollen Distribution at Various Altitudes Critical Design Review, Madison, WI First Row: Tenzin Sonam, John Schoech, Ben Winokur, Henry Wroblewski, Alec Walker Second Row: Connie Wang, Zoë Batson, Ruijun Wang, Maia Perez

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3 Table of Contents Summary of CDR Report... 6 Team Summary... 6 Lead Educators and Mentors... 6 Launch Vehicle Summary... 6 Payload Summary... 6 Changes Made Since PDR... 7 Changes made to Vehicle Criteria... 7 Changes made to Payload Criteria... 7 Changes made to Activity Plan... 7 Vehicle Criteria... 8 Selection, Design, and Verification of Launch Vehicle... 8 Mission Statement... 8 Major Milestone Schedule for Construction... 8 Required Subsystems... 8 Design Integrity and Maturity Verification Plan, Status, and Matrix Recovery Subsystem Mission Performance Predictions Payload Integration Scale Model Launch Operation Procedures Launch system Final assembly and launch procedures Disarming Procedure (only if motor doesn t ignite) Safety and Environment Safety Officer Workshop and Rocket Risks Environmental Concerns

4 Payload Criteria Selection, Design, and Verification of Payload Experiment Payload System Atmospheric and Location Data Collection Subsystem Pollen Collector Subsystem Preparing B1 and B2 for Flight Verification Matrix Verification Plan and Status Preliminary Integration Plan Repeatability and Precision of Instrumentation Safety and Failure Analysis Payload Concept Features and Definition Creativity and Originality Uniqueness and Significance Suitable level of challenge Science Value Science Payload Objectives Payload success criteria Experimental logic, approach, and method of investigation Test and Measurement, variables and controls Relevance of expected data, accuracy/error analysis Preliminary Experiment Process Procedures Safety and Environment Payload Failure Analysis Environmental Concerns Activity Plan Budget Timeline Outreach Conclusion

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6 Summary of CDR Report Team Summary 30 Ash Street Madison, WI Lead Educators and Mentors Christine Hager Pavel Pinkas Brent Lillesand Scott Goebel Rehan Quraishi Peter Culviner Lead Educator, Biology Teacher, West High School Scientific Advisor, NAR HPR Level 1 Certified HPR Mentor, NAR HPR Level 3 Certified HPR Mentor, NAR HPR Level 3 Certified UW Student UW Student Launch Vehicle Summary The launch vehicle has the capacity to carry two payload modules (pollen collectors) to an altitude of one mile (5,280ft). The approximately 11-foot fiberglass rocket of 4- inch diameter will be propelled by a K-class AMW or Aerotech motor. The booster will utilize a standard dual-deployment recovery scheme, while each pollen collector and the payload compartment will have independent parachutes. We will launch our rocket from a 10 foot launch rail. Payload Summary Our experiment will demonstrate the correlation between pollen and atmospheric factors, such as wind speed, temperature, humidity, air pressure and altitude. The atmospheric data will be collected using a GPS module, digital thermometer, hygrometer, digital barometer, and altimeter, respectively. The payload will collect pollen samples during the descent. The collected samples will be analyzed to determine concentration and plant source. Our payload will include two sampling units each containing four Rotorod samplers. Each sampler will be exposed to the airflow at designated altitudes, and then closed with a rotating disk at predetermined time intervals. The samples will be identified and quantified using a compound light microscope. The information obtained during the project will contribute to the current understanding of pollen distribution and its implications on allergies, cross-pollination, and the spread of invasive species

7 Changes Made Since PDR Changes made to Vehicle Criteria Reduced space for the parachutes Recalculated size of the parachutes Reduced allotted space for the payload modules Recalculated predicted masses Added results of the scale model flight Added table of calculated ejection charges Mission performance predictions updated to AMW K975WW motor (our current primary motor choice) Changes made to Payload Criteria Added a more detailed schematics of the atmospheric and location data acquisition and pollen collector controller Changes made to Activity Plan No changes have been made to the Activity Plan, the project progresses according to our original schedule

8 Vehicle Criteria Selection, Design, and Verification of Launch Vehicle Mission Statement Our objective is to launch a vehicle holding two pollen collection modules in a payload compartment to an altitude of 5280 feet (one mile). The success of our objective requires a functioning rocket and its subsystems. A successful mission fulfills the following criteria: a stable launch of the vehicle to the target altitude of one mile separation of the payload compartment from the booster at apogee separation of the pollen collection modules from the payload bay at 4200 feet proper deployment of all parachutes safe recovery of the booster, payload compartment and the two pollen collectors without damage. Major Milestone Schedule for Construction DATE January 29 February 17 February 17 February 23 March 23 March 31 April 5 April 20 April 26 May 23 SUMMARY CDR presentation Full Scale Design Completed Static Testing of Components First test flight of full-scale vehicle without payload (1/2 mi.) Payload completed FRR presentation Final flight test Rocket ready for final launch Launch rocket with all components PLAR due Table 1: Major Milestones Required Subsystems Propulsion System: Our primary motor choice is the Animal Motor Works K975. Alternatives are the Aerotech K1050W, AMW K1075 and the AMW K600. We will use a 75 mm phenolic motor-mount tube, centered in the rocket body with three ¼ plywood centering rings. We will secure the motor with a Lock N Load motor retention system. We will also build an adapter for a 54 mm motor, to keep our motor options open. For our first test flight we will use a J800 by Aerotech, which will propel our rocket to an estimated altitude of 2600 ft. Structural System: The structural system consists of 4 diameter fiberglass tubing. Three fins made of G10 fiberglass will be attached with throughthe-wall construction to the motor mount. Phenolic tubing is not acceptable, as it is too brittle and likely to be damage during the high-power rocket flight

9 Payload Bay System: see Payload Integration section Deployment System: The deployment system will be set up as follows: 1. Booster The booster deployment system will consist of two dual event altimeters, (Perfect Flight MAWDs) with a single ejection charge with two e-matches for the booster drogue and another ejection charge with two e- matches for the main parachute. Both altimeters fire the same charge when each event (apogee, main parachute deployment altitude) occurs. The drogue parachute will deploy at apogee with the separation of the booster from the payload section of the rocket. We have calculated the ejection charge for the drogue parachute at 1 gram. The main parachute will deploy when the booster reaches an altitude of 500 feet. We have calculated the ejection charge for the main parachute at 1 gram also. 2. Payload The payload deployment system will consist of two dual event altimeters (Perfect Flight MAWDs). Both altimeters will fire the same charge from separate e-matches at apogee, deploying the payload bay drogue parachute. This ejection charge has been calculated to 1 gram. One of the altimeters will also provide data to an onboard flight computer which will fire the ejection charge at 4200ft to deploy payload modules (MAWD altimeters cannot fire set-altitude events above 1700ft). The ejection charges for payload deployment have been calculated at 4.5 grams. Our failsafe option will be the other altimeter. It will be programmed to fire an ejection charge at 500 ft. This will result in no useful data, however our sampling equipment will be preserved. a. The Sampling Modules (Bees) The ejection charge placed above the two bees will fire at 4200 ft, ejecting the bees from the main payload bay while simultaneously deploying their parachutes. The two bees will descend under their own main parachutes, thus reducing the weight of the payload bay which will make the drogue parachute sufficiently large to serve as a main parachute. Figure 1: This figure shows our projected flight sequence, including the deployment scheme. 1. Rocket is launched and coasts to an apogee of one mile, 2. At apogee, the payload section, or hive, will separate from the booster, and the booster will immediately deploy a drogue parachute, 3. After descending to an altitude of 700 feet, the booster will deploy the main parachute, 4. Meanwhile, the payload bay, or hive, has also deployed a pilot (drogue) parachute at apogee - 9 -

10 5. The hive descends to 4200ft, the start of the first sampling range (R1) 6. The bees are deployed and continue descend under own parachutes. The hive then continues at a safe descent rate under the same parachute, as it is now much lighter. The Bees sample each altitude range (R1, R2, R3, R4) into a different pollen sampler (Rotorod device) and then rotate to an all-closed position before landing. Recovery System: see below Tracking System: The tracking system will consist of a 140dB screamer in the booster and the payload bay and Walston radio beacon in each pollen collector. Launch System: We will be using a standard 12V launch controller. The launch system will consist of a standard HPR launch tower with a 10-foot rail. Standard sized rail buttons will be used. Design Integrity and Maturity Our Rocket has been designed with the principles of high-power rocketry in mind. We use strong materials, fiberglass for the body, G10 fiberglass for the fins, we are using a through the wall fin mount for extra strength, and we are using a dual deployment scheme for the booster to make recovery easier. We have also taken into account the fact that larger rockets can acceptably handle stability margins significantly over 2.5. Figure 2: RockSim drawing of our rocket, showing center of gravity and center of pressure as determined by the RockSim Stability Method. The stability margin of our rocket is 4.5 (calibers). The center of pressure is inches from the tip of the nosecone. The center of gravity is 90.6 inches from the tip of the nosecone. The rocket has a stability margin of 4.5 calibers. Figure 3: Three dimensional view of the vehicle showing in green the payloads, in blue the e-bays, in gray the parachutes, and in red the motor mount. Figure 4: Schematic view of the vehicle showing 1-payload section, or hive; 2-drogue parachute storage; 3-main deployment electronics; 4-main parachute storage; and 5-motor. (Drawing not to scale)

11 Suitability of fins Fins are of trapezoidal shape with a sufficient semispan, tip and root chords. We have no special performance requirements for the fins (other than to provide sufficient stability). Trapezoidal fins are easy to manufacture and they are not easily damaged during transport and handling. Proper Use of Materials and Proper Assembly Procedures Rocket parts and material are listed in the table below (Table 3). Robustness of the rocket will be provided by fiberglass tubing and couplers, G10 fins, plastic nose cone, plywood centering rings and bulkheads. Attachment points will be ¼ metal U-Bolts and ¼ QuickLinks. Electronic bays will be held together by ¼ threaded rods and electronic components will be mounted on G10 boards. West Epoxy with fillers will be used to assemble the rocket. Fins will be mounted through the wall, anchored at the motor tube and the space between fins will be filled with self-expanding foam. Nylon rail buttons will used to guide the rocket along the launch rail. We will use Kevlar shockcords with Nomex thermal protectors. The parachutes will be made from ripstop nylon and the shroud lines will be nylon strings. Rocket Parts Plastic Nose Cone 1/8 G-10 Fiberglass Fins 4 Fiberglass Body 75mm Motor Mount (phenolic) Three ½ Plywood Centering Rings (to Lock N Load Motor Retention System secure motor mount) ¼ Tie Rods Fiberglass Tube Couplers Igniters Motor Rip-Stop Nylon Elastic Parachutes Kevlar Shock Cord ¼ Metal U-Bolts ¼ Metal I-Bolt ½ Plywood Bulkheads Ejection Charges G-10 E-bay Board Altimeters 9 Volt Batteries Cable Ties Switches 54 mm Engine Casing Fiberglass E-Bay Ring Nylon Rail Buttons Table 1: Rocket Parts Motor Retention We will use Lock N Load motor retention system (this system consists from an outer thread installed on the bottom of the motor mount tube and an screw-on cap that hold the motor in. Lock N Load motor retention has been successfully used by our previous SLI teams

12 Verification Plan, Status, and Matrix 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 fits smoothly and snuggly 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: Screamers, beacons C11: Shock cords and anchors C12: Rocket stability

13 Matrix Legend P: Planned Tests F: 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 F P C 2 F F F F F C 3 P P P P C 4 P F F P P C 5 P F C 6 P F P P P C 7 F P F F C 8 F F F C 9 P F P C 10 F F F C 11 P F F C 12 F F Table 2: Verification Matrix Recovery Subsystem Our rocket will deploy a total of five parachutes. The two parachutes on the booster section will use a standard dual deployment scheme, ejected by one charge fired by two altimeters with separate e-matches per parachute. Each charge will be connected to two dual-event altimeters for redundancy. The payload bay will have one parachute that will maintain a safe landing descent rate after the bees have ejected, about 20 ft/sec. Each pollen collector will also have its own parachute. All five parachutes will be commercially available rip-stop nylon parachutes with nylon shroud-lines. The dimensions of these parachutes and the rocket component descent rates will be as follows: Component Weight Parachute Diameter Descent Rate Ejection charge Booster (Drogue) 196 oz. 24" 47 ft/sec 1.0g (FFFF) Booster (Main) 196 oz. 62'' 18 ft/sec 1.0g (FFFF) Payload Bay (Full) 133 oz. 24" 39 ft/sec 1.0g (FFFF) Payload Bay (Empty) 37 oz. 24" 20 ft/sec N/A Pollen Collector 48 oz. 34" 16 ft/sec 4.5g (FFFF) Table 3: Parachute dimensions for individual components. NOTE: 4.5g of FFFF black powder will be used to expel both pollen samplers (B1 and B2) out of the payload section (hive)

14 Ejection charges are calculated using the following formula: Wp = dp * V / R * T where Wp ejection charge in pounds of black powder dp ejection pressure (15 psi) R combustion gas constant (22.16ft/lbf/lbm o R) T combustion temperature (3307 o R) V free volume in cubic inches The results of ejection charge calculation will be used as a starting point for static ejection tests. The amounts of the black powder needed for successful ejection may differ from the results of the calculations and will be determined by static testing. Mission Performance Predictions Our rocket will fly to an altitude of one mile and separate into four different sections. The payload bay will descend under a parachute to 4200 ft, where it will deploy the pollen sampling devices. The booster will deploy a drogue parachute at apogee and a main parachute at an altitude of 500 ft. Figure 5: Thrust curve for Animal Motor Works K975WW, our projected motor. The rocket will have a peak thrust of 1150 N at 0.03 seconds, continues burning for 1.6 seconds at a thrust of about 1150 N, and burns out at 2.5 sec

15 Figure 6: This graph shows the acceleration over time. The acceleration value increases to a maximum of 13 gee's, over a period of about 1.7 seconds. Figure 7: This graph shows the altitude vs. time flight profile as projected by RockSim (Animal Motor Works K975WW)

16 MOTOR WIND SPEED (MPH) APOGEE PERCENT CHANGE K-975W K-975W K-975W K-975W K-975W Table 4: Variation of altitude with regard to wind speed -- We run simulations of our projected rocket design at different wind speeds so that we can determine whether or not our rocket weather-cocks too much, and therefore wouldn t reach our target altitude under windy conditions. Due to inaccuracies of RockSim, and prior experience, we believe that estimated altitudes need to be 5-10% higher than the actual target altitude. Payload Integration The rocket will consist of two components, the vehicle itself and the payload module. The payload will be constructed within a coupler tube, so that it fits smoothly into the outer frame of the rocket. The body of the payload and the inner components are constructed of materials strong enough to withstand the forces of acceleration of the motor. Furthermore, the inner components of the payload are also properly secured to prevent excess agitation during flight. The payload is only dependant on the rocket to transport it to the deployment altitude. Upon ejection, the payload module is completely autonomous of all other systems. Figure 8: Payload integration scheme. The payload parachute is stored behind the nosecone and deployed at apogee by an ejection charge above the payload electronic bay. The payload parachute will act as a drogue parachute first, allowing for a quick controlled descent of the payload section to the altitude of 4,200ft.The pollen collectors are deployed at altitude of 4,200ft by an ejection charge below the payload electronics bay. Deploying both collectors will decrease the mass of the payload section and the payload parachute now becomes a main parachute for the empty payload section. The pollen collectors descend under their own parachutes

17 Scale Model On January 12 we conducted a test flight with our scale model. The purpose of this test flight was to determine the stability of our rocket and to test our rocket separation and payload deployment scheme. We paid particular attention to the deployment of our two dummy pollen collection modules. Both of these dummy modules were designed to be ejected from the payload bay at a given altitude (postapogee) and descend under separate parachutes. We needed to be certain that the modules will remain in the payload bay during apogee separation and then deploy without tangling at the set altitude. Scale Model Parameters Liftoff Weight: Motor: Length: Diameter: Stability Margin: Scale Model Flight Events Booster Drogue: Payload Section Separation: Booster Main Parachute: Payload modules deployment: Scale Model Flight Results Apogee: Time to apogee: Apogee events: Payload deployment: Booster main parachute: 3980g Aerotech I366R 103 inches 2.6in (BT80 Quantum tubing) 7 calibers Apogee Apogee 500ft 300ft 2091ft (Rocksim Prediction: 1884ft) 11s 1.5s after apogee 300ft at 75s 500ft at 23s We flew our scale model on an AeroTech I-366R. Our flight was straight with little noticeable weather cocking. We also noticed a slight wobble in the center of the rocket (similar to that of an arrow). However, this did not affect the stability of our rocket and was actually caused by a loose coupler. For our final vehicle we will be using fiberglass for the coupler and the body, manufactured for a proper fit. The projected altitude for this flight was 1884 feet and the actual altitude of the flight was 2091 feet. All four of the rocket s ejection events occurred as planned. Our dummy payload modules deployed cleanly and descended safely, despite the fact that some of the shroud lines parted. This was because they were custom made parachutes, for our final model we will use commercially manufactured parachutes to prevent this. We also had a problem with our booster section parachute deployment. We failed to remove a rubber-band (used to keep the parachute folded during rocket flight preparation) from the drogue parachute. We will prevent this by writing and following a detailed checklist. Consequently, the drogue on the booster section did not fully deploy and our rocket descended at a higher rate than planned. This also caused the stripping of the main parachute. The break in shroud line occurred at the elastic. Despite the stripping of the main parachute, our booster landed with only minor damage

18 Data were collected by four MAWD altimeters, two altimeters placed in the booster section e-bay and the remaining altimeter residing in the payload section e-bay. The altimeters were also used to fire ejection charges for all flight events. The altimeters functioned perfectly, all charges were fired and each altimeter recorded an altitude vs. time profile. Altitude vs. Time A B Altitude (ft.) Booster 1 Booster 2 Payload 1 Payload C E 0 D Time Figure 9: This graph shows the altitude of our flight over time. Point A is apogee at 11 seconds and 2090 feet after ignition. Point B is separation of the rocket and deployment of drogue parachutes at 14 seconds and 1980 feet. Point C is altimeter initiated deployment of the booster s main parachute, at the programmed altitude of 500 feet 23 seconds after ignition. Point D is the landing of the booster at 32 seconds after the ignition. Point E is the altimeter initiated deployment of the payload modules, at the programmed altitude of 300 feet 75 seconds after ignition. Point F is the landing of the payload bay at 92 seconds after ignition. F Description Initial point Ending point Descent Rate (time, altitude) (time, altitude) Descent of booster without B (14.5, 1980) C (23, 500) ft/sec parachute Descent of booster with stripped C (23, 500) D (32, 0) 55.6 ft/sec main parachute Descent of loaded payload bay B (14.5, 1980) E (75, 300) 27.6 ft/sec Descent of empty payload bay E (75, 300) F (92, 0) 18.2 ft/sec Table 5: Measured descent rates The table above shows the descent rates measured during the scale model flight. It is notable, that the apogee detection occurred 1 second past real apogee. Because

19 of the non-deployment of the drogue parachute, the initial descent of the booster section was very fast, possibly contributing to the stripping of the main parachute. On the other hand, the recovery of the payload section was flawless. The payload section parachute first provided fast but constant rate descent to 300ft where the payload modules were deployed. After the deployment of payload modules the descent rate of the empty payload section dropped by a third thus allowing for soft landing within the recommended 15-20fps landing speeds. Measured and Simulated Ascent to Apogee Altitude (feet) Booster 1 Booster 2 Payload 1 Payload 2 Simulation Time Figure 10: This graph shows measured and predicted ascent to apogee. We were surprised to find that our rocket actually traveled higher than RockSim simulations predicted. Reasons for discrepancies between measured and simulated altitude: Motor variation from simulation thrust curve Slickness of Quantum tubing Inaccuracies in altimeters

20 Figure 11: This picture shows our scale model as it lifts off the launch pad. The red flame from the I-366 Redline motor is well visible. We launched at Bong State Recreation Area

21 Launch Operation Procedures Launch system We will be using a standard launch rail 10 feet in length with a blast shield at the launch pad base. Final assembly and launch procedures 1. Receive assembled payload from payload team 2. Attach parachutes to payload with shock cords 3. Replace batteries in e-bays and test functionality 4. Test continuity on all ejection charges 5. Attach ejection charges to e-bays 6. Attach all permanent joints with screws 7. Fold parachutes properly and insert parachutes and payloads into payload bay with Nomex protection 8. Attach shock cords to main and drogue parachutes and to rocket 9. Fold parachute properly and insert into rocket with Nomex protection 10. Fully assemble rocket and check structural integrity 11. Insert motor into motor mount and secure with motor retention system 12. Place rocket onto launch rod and make sure the rocket slides smoothly 13. Place igniter into the rocket and place engine cap over the end to secure it in place 14. Attach the igniter to the launch system and check for continuity 15. Activate electronics, wait for boot and confirm continuity 16. Move 200 feet away from the rocket (minimum safe launch distance of K- class vehicles) 17. Check sky for aircraft 18. Arm ignition system 19. Countdown 20. Launch rocket Disarming Procedure (only if motor doesn t ignite) 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. Replace igniter 5. Place rocket back on pad, re-arm electronics 6. Test continuity Safety and Environment Safety Officer Zoe Batson will be the safety officer for both the vehicle sub-team and the payload sub-team

22 Workshop and Rocket Risks WORKSHOP RISKS Risk Consequence Mitigation Laceration All members will follow safety procedures to minimize risk Physical Risk (Saws, Knives, Dremel tools, Band Saw) Physical Risk (sandpaper, Fiberglass) Physical Risk (Drill Press) Physical Risk (Soldering Gun) Physical Risk (Computer, Printer) Toxicity Risk (Epoxy, Enamel Paints and Primer, Superglue) Toxicity Risk (Superglue, Epoxy, Enamel Paints and Primer) Abrasion Puncture Wound Burns Electric Shock Toxic Fumes Toxic Substance Consumption All members will follow safety procedures to minimize risk All members will follow safety procedures to minimize risk All members will follow safety procedures to minimize risk All members will follow safety procedures to minimize risk Area will be well ventilated and there will be minimal use of possibly toxicfume emitting substances All members will follow safety procedures to minimize risk ROCKET RISKS Risk Consequence Mitigation Unstable rocket Errant flight, no data collected Rocket stability will be verified by computer and scale model flight Improper motor mounting Damage or destruction of rocket. Engine system will be integrated into the rocket under proper supervision and used in the accordance with the manufactures recommendations. Rocket structure Rocket structural Rocket will be constructed with Propellant malfunction failure Engine explosion 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. Parachute Parachute failure Parachute Packaging will be double checked by team members. Deployment of parachutes will be verified during static testing. Shock Cord Breakage Rocket falls at high speed, damage to rocket Shock cords will be commercially available, tested designs rated for our rocket

23 ROCKET RISKS Risk Consequence Mitigation Payload integration setup will fall apart; pollen samplers will not be able to sample air and may receive possible damage. Payload integration failure Payload deployment will be thoroughly tested during static testing. Launch rail failure Errant flight NAR Safety code will be observed to protect all member and spectators Separation failure Payload ejection charge does not ignite Ejection falsely triggered Tracking/Recovery Failure Part shipments delayed Winter break, students may be on vacation Parachutes and payloads fail to deploy. Payload and its parachute do not deploy. Unexpected/premature ignition/personal injury/property damage Samples and sampling data are lost. Construction delayed Construction delayed Table 6: Risks, consequences and mitigations Separation joints will be properly lubricated and inspected before launch. All other joints will be fastened securely. Two different altimeters will fire the ejection charges (deployment redundancy). Proper arming and disarming procedures will be followed. External switches will control all rocket electronics. Two different sampling payloads will be released. If one is lost, there will still be some data collected. Each payload will be equipped with both a radio and a sonic tracking beacon to facilitate rocket location and recovery. Parts will be ordered in advance Meetings will be planned when enough members can attend to have a productive session

24 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 non-biodegradable 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

25 Payload Criteria Selection, Design, and Verification of Payload Experiment Payload System Our payload is designed to collect airborne pollen grains. A special sampler is necessary for collection of the pollen, as the pollen grains are very small and easily avoid capture. The collected pollen samples will be examined under a microscope for pollen types and amounts. The journey of pollen through our experiment is depicted on the picture below. Figure 12: Journey of Pollen. 1. Plants release pollen grains into the atmosphere. 2. Our sampling devices, B1 and B2, collect these as they make their descent down from their flight. 3. The rotating forks trap pollen grains passing through the sampling devices. 4. We will examine the forks using microscopes. 5. We will count the number of pollen grains on each fork and we will also attempt to identify the pollen types. 6. The data collected will be used summarized in graphs and tables in our final report. The payload consists of two major subsystems: the electronics board for collection of atmospheric and location data and the four-chambered pollen sampler, each chamber collecting pollen through a specific altitude range. For a successful experiment, both subsystems need to function properly as described in the sections below. Both subsystems were designed after consulting with experts and the details of each subsystem are described later in the document. Atmospheric and Location Data Collection Subsystem We will design, build and program an electronic board for collection of atmospheric and location data. Temperature (T), humidity (H), pressure (P), altitude (A) and location (Z) will be sampled every second and stored in the onboard non-volatile memory (EEPROM type). In addition to the atmospheric and location data acquisition, the board will also control switching of the Rotorod pollen samplers inside each pollen collector (this includes rotating the selector funnel to a desired position and switching on/off the motor that rotates the sampling fork inside each pollen sampler). As of now, we do not plan to utilize the board for deployment purposes

26 Figure 13: shows the four different sensors (thermometer, hygrometer, pressure sensor, GPS) which will communicate the collected data to the CPU. Once the CPU receives the data, it is transmitted to the EEPROM memory module for permanent (non-volatile) storage. The data will be extracted from the EEPROM memory after the flight for further processing. Figure 14: An approximate electrical schematic showing important connections between the chips we plan to use for atmospheric and location data collection

27 The major electronic components for our data collection purposes are listed in the table below. ATMOSPHERIC DATA AND LOCATION ELECTRONIC COMPONENTS Sensor/Chip Type Model Price Accuracy GPS Parallax GPS Receiver Module $69.95 ±5 meter position, ±0.1 meter per second velocity Pressure Freescale Semiconductor $17.70 ±1.5% over 0 to 85 C MPXA6115A6U Temperature/Humidi Sensirion SHT11 Humidity ty & Temperature Sensor Microcontroller/CPU Parallax Propeller I P8X32 $14.95 N/A 32KB Serial 24LC256 $2.95 N/A EEPROM Memory $29.95 ± C, ±3.5%RH Cost: $ per board, $ total Table 7: Major electronic components for data collection and pollen collectors operation The CPU (Parallax Propeller I P8X32 chip) is an octa-core 32bit microprocessor with floating point software capabilities. This will allow us to store the measured data in a single precision floating point format, thus eliminating the need for further data conversion after the flight. Temperature (T), humidity (H), pressure (P) and location (Z, three coordinates) will be all stored as floating point numbers, 32 bits wide (IEEE format). The index of active pollen sampler will be stored as an unsigned byte variable (8 bits). This results in size of a single data record being 25 bytes. Figure 15: Data storage requirements and data structure

28 The readings are taken every second and the projected flight duration is 372 seconds. Therefore, 9300 bytes will be needed to record all of the data for one flight. As not to lose any data due to an unexpectedly long flight, we have designed for twice the projected flight duration. As there is no 18.6 kb memory chip available, we will use a standard 32kB 24LC256 EEPROM chip. Pollen Collector Subsystem The pollen grains will be collected by the pollen collection subsystem. This subsystem consists of four independent Rotorod type pollen samplers, each sampler collecting pollen through a specific altitude range. The operational and functional principles of a Rotorod pollen sampler are described and explained later in this document. The figure on next page shows the assembly of a pollen collector. Figure 16: Pollen collector assembly 1. Servo rotating the fan and selector funnel to each individual collection tube. This allows the fan to draw air only through one tube at a time. 2. Fan drawing air through the pollen sampler tubes (one sampler at a time). 3. Selector funnel that keeps the fan from drawing air from the other tubes (directs the air through a selected sampler only). 4. Fans which will serve as motors for our sampling forks. They will spin at a speed 2400 rpm or higher. That way, they have a higher probability of hitting the airborne pollen grain and collecting it. 5. Sampler tube which will hold the tuning forks. 6. Sampling forks, coated with silicon gel will collect the pollen grains as it is drawn through the sampler tube. 7. Selector disk which will rotate to select the tubes that will have air drawn through them (the disk is synchronized with the selector funnel). 8. Servo operating the selector disk. 9. Wires connecting the fans and servos to the control electronics. 10. Control electronics bay which controls the rest of the subsystems

29 Figure 17: Pollen collector footprint The major dimensions of the pollen collector and pollen samplers are identified on the picture on the left. The pollen collector will be enclosed in a 4 tube coupler (inner diameter of the coupler is ). To fit four pollen samplers inside the collector, the maximum possible outer diameter of a pollen sampler tube is 1.5. The major components of pollen collectors are listed in the table below. POLLEN COLLECTOR PARTS Item/Amount Name of Item Specifications Price 2x Air Volume Fans Sunon 80 mm $13.99 per fan (PMP1208PMB1) 84.1 Feet Per Second RPM 8x Fork Rotating Evercool EC mm $3.99 per fan Fans 4x Servo (rotating selector mechanism) 2x Custom made funnel selector disk 2x Payload Tube 8x Polycarbonate tube (pollen sampler body) Parallax Mini Servo ( ) Funnel selector 4 inch Coupler Tube Polycarbonate Tube Table 8: Pollen collector parts 8000 RPM 180 degree rotation, modified for 360 degree rotation Paper funnel with fiberglass/epoxy coating Phenolic tubing 1.5 OD/ 1/16 wall 1ft long $15.00 per servo N/A ~$5.00 per coupler ~2.50 per tube Cost: $74.95 per collector, $ total The payload will include two pollen collectors, dubbed Bee 1 (B1) and Bee 2 (B2). Each collector will hold four Rotorod pollen samplers (see Figure 16 for overall scheme of pollen collector). Each collector will sample the same set of altitude ranges to give us redundancy in data collection. A selector disk keeps one Rotorod open and the others closed at any given time in each collector. A fan will pull air through the open Rotorod sampler. This sampler will then collect pollen with the spinning fork coated in silicone gel. The fork spins at rpm. The gel with the trapped pollen grains can then be examined under a microscope to determine pollen counts and types

30 Preparing B1 and B2 for Flight 1. Rotate the servo, checking that nothing is obstructing its path 2. Rotate each of the fans to see that the sampling forks are secure 3. Attach parachutes to B1 and B2 4. Properly fold the parachutes and wrap them in Nomex cover 5. Switch on electronics for B1 and B2 6. Carefully place B1 and parachute into the rocket 7. Carefully place B2 and parachute into the rocket 8. Check that both B1 and B2 are sliding freely inside the hive 9. Cap the hive on the bottom with the tube coupler 10. Connect the hive with the booster section 11. Check that rocket sections will separate properly and smoothly

31 Verification Matrix The components and tests as well as the matrix showing the components and the tests they will be subject to are listed below. Components to be Verified 1. Fan (to draw the air through pollen samplers) 2. Servomotor (to rotate the selector discs) 3. Selector Disc 4. Rotorod Motor 5. Rotorod Fork 6. Altimeter 7. Thermometer 8. Hygrometer 9. GPS 10. Atmospheric Pressure Sensor 11. Battery Pack Verification Tests 1. Drop Test: to evaluate the structural integrity of the component 2. Pollen Capture Test: verify the ability to capture pollen particles (we will grow our own pollen for this test) 3. Connection Test: to determine whether or not the component can be connected to battery pack 4. Battery Capacity Test: verify that the battery has enough capacity to run the pollen samplers and sensor board for the duration of flight. 5. Pressure Chamber Test (Calibration): verify that pressure sensors register the pressure changes correctly 6. Scale Model Flight: where possible, include the component in scale model flight to verify that the component can function during rocket flight 7. Heating Test (Calibration): verify that the digital thermometer register the temperature changes correctly 8. Cooling Test (Calibration): similar to test #7 9. Humidity Test (Calibration): verify the the humidity sensor registers the humidity changes correctly 10. GPS Ground Test (Calibration): to determine whether or not the component gives right coordinates. 11. Acquisition Test: to determine whether or not the GPS component can pick up satellites. 12. Durability Test: operate the component for an hour to determine whether or not the component can withstand the stress. 13. Air Flow Test: verify the fan produces sufficient flowrate (at least 1m 3 per sampling range

32 Legend P- Planned F- Finished Component Test P P P P 2 P P P 3 P P 4 P P P 5 P P 6 P P P F 7 P P P P 8 P P P 9 P P F P P 10 P P P 11 P P Table 9. Payload Verification Matrix Verification Plan and Status As previously described in the verification matrix, all planned tests have yet to be conducted. The successful completion of all tests will determine the payload flight readiness. Preliminary Integration Plan Refer to the Payload Integration Plan in the vehicle section. Repeatability and Precision of Instrumentation Two sampler modules will collect pollen at the same altitude ranges during each flight; and we will expect the data from both samplers to be similar. Commercially available sensors will be used for the collection of atmospheric data. These sensors have been factory- calibrated and their accuracy is described in the specification sheets. We will also verify and calibrate these sensors as described in the verification matrix. The accuracy for each device is noted in the subsystems section of this document. Safety and Failure Analysis Refer to Safety and Environment in the payload section

33 Payload Concept Features and Definition Creativity and Originality While researching the distribution of pollen in the atmosphere, team members came upon an interesting article revealing differences in pollen concentrations at different altitudes that inspired us to build upon these findings. Although rocketry members from West High School have previously contemplated the idea of air sampling, it was not until this team s research that we have discovered a feasible sampling technique. Using this sampling technique, we will not only be observing the correlations between pollen concentration and altitude but also the possible correlations with other atmospheric factors. Furthermore, we will identify the different species of pollen present in our samples at different altitudes. Uniqueness and Significance High altitude pollen sampling will provide information on pollen distribution patterns which affect cross-pollination and the spread of invasive plant species. Correlations between atmospheric factors and pollen distribution will also add to the understanding of the effects of climate change on cross-pollination. Sampling pollen at two diverse launch sites (Kenosha, WI and Huntsville, AL) will provide data from which we can determine similarities and differences in pollen concentrations of different species at corresponding altitudes. Furthermore, as described below, our sampling device will be able to collect sufficient amounts of pollen during the descent by utilizing a fan to draw in enough air and a high speed rotating fork coated with silicone gel to trap the pollen grains. Suitable level of challenge Capturing pollen is a complex challenge which requires us to design and build a creative sampling system. Pollen particles are extremely small, (some as small as 6μm) and are therefore difficult to direct to a trap. During peak season, the expected concentration range is only about pollen grains per cubic meter. The difficulties of pollen sampling and the solution are explained in Figures 14, 15 and 16. Figure 18: This air sampling technique is traditional for capturing larger particles. Air flow is directed toward a wall coated with adhesive, which serves on a trap. Because of the small size of pollen grains, this traditional air-sampling technique does not work for pollen collection. Instead of being trapped on the wall, the pollen grains stay in the airflow and avoid obstacles

34 Figure 19: Increasing the airflow rate with a pump can allow the trapping of pollen particle, as they are not able to stay with the airflow and collide with the adhesive coated wall. However, the cost and size of air pumps with sufficient flow rate make this technique cost-prohibitive for us. Figure 20: This drawing shows a rendering of our proposed pollen sampler (Rotorod type). The fan at the top draws air through so that it can be sampled by the spinning fork. The fork will spin at 2,400 rpm (or faster), simulating the high speed jet of the traditional sampler, as shown in Figure Incoming air and pollen particles (the air leaves the pollen sampler through the fan on the top of the sampler) 2. Fan drawing the air through the collector. 3. Rotating fork, each arm is being equipped by a strip coated with adhesive for trapping the pollen particle 4. Pollen particles. In order to capture a sufficient number of pollen grains, we will use a Rotorod type sampler system which will allow us to process one or more cubic meters of air per sampling range. The proposed technique has been thoroughly researched and is based on industrial standards for pollen collection. The feasibility of our project has been verified by literature research and discussions with the researchers at UW, Madison. Evaluating pollen samples under a microscope is a skill and time demanding process. The entire team, supervised a microscopy specialist, will participate in the final analysis of the collected samples. High quality microscopes (Zeiss and Nikon brands) have been allocated for the final analysis at Dept of Zoology, UW Madison

35 Science Value Science Payload Objectives According to a study conducted in 1999 in León, Spain, (Comtois et al., 1999) a correlation exists between the atmospheric factors of altitude and temperature and pollen concentration. A higher concentration of pollen was reported at an altitude of 600 meters (approx 2000 feet) as compared to ground level. We will sample the air at higher altitude ranges and record other atmospheric factors, such as humidity, wind speed and direction, as well as air pressure to determine further correlations between atmospheric factors and pollen concentration. Payload success criteria Rotorod devices function at the four altitude ranges and are recovered undamaged. Pollen particles adhere to the silicone gel. Payload collects measurable amounts of pollen. Independent variable sensors reliably measure and record atmospheric data. Experimental logic, approach, and method of investigation From the atmospheric data collected by the payload and the analyses of the pollen samples, the primary correlation will be the correlation between the distribution of pollen and the altitude range. Y x = f(a) or Y = f(a) Other correlations between the amount of a specific type of pollen and the individual environmental factors of temperature, humidity, air pressure, and wind speed will also be identified. Y x = f(t). pollen type X amount vs. temperature Y x = f(h). pollen type X amount vs. humidity Y x = f(p). pollen type X amount vs. pressure Y x = f(z). pollen type X amount vs. location/wind speed Additional correlations could be the correlations between these atmospheric factors and the total amount of pollen. Y = f(t), Y = f(h), Y = f(p), Y = f(z) Further analysis of the pollen samples may also lead to the identification of correlations between the distribution patterns and multiple variables and also correlations between environmental variables. The aforementioned relationships will

36 provide us with a better understanding of the pollen migration and what factors affect the pollen distribution in the atmosphere. Test and Measurement, variables and controls The rocket will be sent to an altitude of 1 mile, and the pollen collectors will be deployed at 4200 ft. These two collectors will sample air at four predetermined altitude ranges in four containers, each corresponding to one altitude range, using a Rotorod-like device to collect the pollen. After the flight, the Rotorod sampling bars will be taken back to a university microscopy lab for quantitative analysis. They will be stained by a suitable dye to make the pollen visible. We will then inspect the sampling bars under a microscope with a magnification of 100x lens and 10x ocular to determine the amount and species of pollen collected. Test Amount of pollen Species of pollen Measurement Pollen grains will be viewed and counted individually under a microscope Pollen grains will be identified by using suitable manuals and other identification keys 1 Table 10. Ascribed tests for each sampler at prescribed altitudes. 1 Suitable sources for pollen identification: Sampling and Identifying Pollens and Molds An Illustrated Identification Manual for Air Samplers E. Grant Smith, 1990 Blewstone Press P.O. Box 8571 San Antonio, Texas Dichotomous Key: List of Identification Resources:

37 Independent variables are T..air temperature H..humidity P..atmospheric pressure A..altitude range Z..GPS position X..pollen type Dependent variables are Y x...amount of pollen of a specific type Y.. total amount of pollen Controls are Identical collection process Identical methods of counting Selected altitude ranges Relevance of expected data, accuracy/error analysis The correlations gathered in this experiment will aid in the understanding of the influence of various environmental factors on cross pollination. These correlations are important because some plants rely on air-borne pollen for cross pollination and the production of fruit. Therefore, a change in environmental factors, such as those caused by climate change, could possibly cause major disturbances for these plants. If the plant colonies in the vicinity of the pollen collection area are determined, the data will also provide information on the distances travelled and possible destinations of the pollen, the cross pollination between two colonies of similar species, and the spread of invasive species. Correlations between environmental factors and pollen concentration will also aid in determining the atmospheric conditions that increase pollen concentration and thus worsen outdoor allergies. Two sampler modules will collect pollen at the same altitude ranges during each flight; and we will expect the data from both samplers to be similar. Commercially available sensors will be used for the collection of atmospheric data. These sensors have been factory- calibrated and their accuracy is described in the specification sheets. We will also verify and calibrate these sensors as described in the verification matrix. The accuracy for each device is noted in the Subsystems section of this document