1. Bacteria Hunters Bacterial Concentrations Above and Below the Planetary Boundary Layer

2. Part 1 Vehicle

3. Major Milestones Schedule March 21 st Second full scale launch March 22 nd Payload completion and testing March 28 th All-Systems-Ready for SLI launch April 2 nd FRR presentation April 19 th SLI launch May 10 th Payload analysis complete May 22 nd PLAR due

4. Flight Sequence 1.Rocket launches 2.Rocket reaches apogee 3.Drogue parachute deploys 4.Main parachute deploys 5.Above boundary layer sample (S 1 ) 6.Below boundary layer sample (S 2 ) 7.Near ground sample (S 3 ) 8.Rocket lands TRACKING & RECOVERY: because of possible long drift, on-board sonic and radio beacons will be used to help us with tracking and recovery.        

5. Success Criteria Stable flight of the vehicle Stable flight of the vehicle Target altitude of 5,280ft reached Target altitude of 5,280ft reached Payload delivered undamaged Payload delivered undamaged Proper deployment of all parachutes Proper deployment of all parachutes Safe recovery of the vehicle and the payload without damage Safe recovery of the vehicle and the payload without damage

6. Full Scale Rocket CP98.329” (from nosetip) CG81.908” (from nosetip) Static Margin4.11 calibers Length124.25” Diameter4.0” Liftoff weight22.5 Pounds MotorAerotech K700W RMS CG CP

7. Construction Materials Fins: 1/8” balsa between 1/32” G10 fiberglass Fins: 1/8” balsa between 1/32” G10 fiberglass Body: fiberglass tubing, fiberglass couplers Body: fiberglass tubing, fiberglass couplers Bulkheads: 1/2” plywood Bulkheads: 1/2” plywood Motor Mount: 54mm phenolic tubing, 1/2” plywood centering rings Motor Mount: 54mm phenolic tubing, 1/2” plywood centering rings Nosecone: commercially made plastic nosecone Nosecone: commercially made plastic nosecone Rail Buttons: standard size nylon buttons Rail Buttons: standard size nylon buttons Motor Retention System: Aeropack screw-on motor retainer Motor Retention System: Aeropack screw-on motor retainer Anchors: 1/4” stainless steel U-Bolts Anchors: 1/4” stainless steel U-Bolts Epoxy: West System with appropriate fillers Epoxy: West System with appropriate fillers

8. Motor Retention Aeropack Tailcone Motor Retainer

9. Thrust Profile for K700W

10. Acceleration Profile for K700W

11. Altitude Profile for K700W

12. Projected Drift mph528050004000300020001000900 00.0 ft 53,097 ft2,960 ft2,470 ft1,918 ft1,491 ft1,001 ft952 ft 106,195 ft5,921 ft4,941 ft3,962 ft2,983 ft2,003 ft1,905 ft 159,292 ft8,881 ft7,412 ft5,943 ft4,474 ft3,005 ft2,858 ft 2012,390 ft11,842 ft9,883 ft7,924 ft5,966 ft4,007 ft3,811 ft Main deployment Altitude Wind speed

13. Flight Safety Parameters Stability static margin: 4.11 Stability static margin: 4.11 Thrust to weight ratio: 6.85 Thrust to weight ratio: 6.85 Velocity at launch guide Velocity at launch guide departure: 84.6fps

14. Ejection Charge Calculations W = dP * V/(R * T) Where: dP = ejection charge pressure, 15 [ psi ] dP = ejection charge pressure, 15 [ psi ] R = combustion gas constant, 22.16 [ ft-lb o R -1 lb-mol -1 ] R = combustion gas constant, 22.16 [ ft-lb o R -1 lb-mol -1 ] T = combustion gas temperature, 3307 [ o R ] T = combustion gas temperature, 3307 [ o R ] V = free volume [ in 3 ] V = free volume [ in 3 ] W = ejection charge weight [ lbs ] W = ejection charge weight [ lbs ]

15. Calculated Ejection Charges Parachute Ejection charge (FFFF black powder) Main Parachute 60 grains (3.89 grams) Drogue Parachute 35 grains (2.27 grams) Ejection charges were verified in static testing and during the test flight. All parachutes deployed.

16. ParachutesParachuteDiameter[in] Descent weight [lbs]DescentRate[fps] Drogue16”20.1575.6 Main84”20.15 12.5 12.5

17. Verification Matrix: Components Tested components: C1: Body (including construction techniques) C1: Body (including construction techniques) C2: Altimeter C2: Altimeter C3: Data Acquisition System (custom computer board and sensors) C3: Data Acquisition System (custom computer board and sensors) C4: Parachutes C4: Parachutes C5: Fins C5: Fins C6: Payload C6: Payload C7: Ejection charges C7: Ejection charges C8: Launch system C8: Launch system C9: Motor mount C9: Motor mount C10: Screamers, beacons C10: Screamers, beacons C11: Shock cords and anchors C11: Shock cords and anchors C12: Rocket stability C12: Rocket stability

18. Verification Matrix: Tests Verification Tests: V1 Integrity Test: applying force to verify durability. V2 Parachute Drop Test: testing parachute functionality. V3 Tension Test: applying force to the parachute shock cords to test durability V4 Prototype Flight: testing the feasibility of the vehicle with a scale model. V5 Functionality Test: test of basic functionality of a device on the ground V6 Altimeter Ground Test: place the altimeter in a closed container and decrease air pressure to simulate altitude changes. Verify that both the apogee and preset altitude events fire (Estes igniters or low resistance bulbs can be used for verification). V7 Electronic Deployment Test: test to determine if the electronics can ignite the deployment charges. V8 Ejection Test: test that the deployment charges have the right amount of force to cause parachute deployment and/or planned component separation. V9 Computer Simulation: use RockSim to predict the behavior of the launch vehicle. V10 Integration Test: ensure that the payload fits smoothly and snuggly into the vehicle, and is robust enough to withstand flight stresses.

19. Verification Matrix V 1 V 2 V 3 V 4 V 5 V 6 V 7 V 8 V 9 V 10 C 1 FFFF C 2 FFFFF C 3 PPPP C 4 FFF C 5 FF C 6 PP C 7 FFFFFF C 8 FF C 9 FF C 10 F C 11 FFFFF C 12 FF

20. Test Flights Results

21. Full Scale Vehicle Test Flight

22. First Full-Scale Vehicle Launch Conclusions Observations The rocket flew to a height of 1586 ft The simulated apogee was 2470 ft Rail button missing after flight The motor nozzle has been damaged The rocket is too heavy Improvements Made Rocket shortened and lightened Second full-scale launch made with full-size motor to accurately determine ability of rocket to reach target altitude

23. Second Full Scale Vehicle Flight Objectives Met Modified vehicle design tested Modified vehicle design tested New parachute sizes tested New parachute sizes tested Ejection charge calculations tested Ejection charge calculations tested Dual-deployment scheme tested Dual-deployment scheme tested Validity of simulation results tested Validity of simulation results tested Rocket stability tested Rocket stability tested

24. Full Scale Model Parameters (after modifications) Liftoff Weight: 24.00 pounds Liftoff Weight: 24.00 pounds Motor: Aerotech K700W Motor: Aerotech K700W Length: 10.35 ft Length: 10.35 ft Diameter: 4” Diameter: 4” Stability Margin: 4.11 calibers Stability Margin: 4.11 calibers

25. Test Flight #2 Results Apogee: 5071ft Apogee: 5071ft Rocksim prediction: 4800 feet Rocksim prediction: 4800 feet Time to apogee: 17.15s Time to apogee: 17.15s Drogue parachute: apogee at 17.15 s Drogue parachute: apogee at 17.15 s Main parachute: 900ft, 72.3s Main parachute: 900ft, 72.3s

26. Test Flight Data Apogee (drogue deployment) Main parachute deployment

27. Test Flight Results Description Start time and start altitude End time and end altitude Descent rate Vehicle under drogue 17.15 s 5071ft 72.3s 900ft 75.6 fps Vehicle under main 72.3s 900 ft 144.2s 0 ft 12.5 fps

28. Payload Integration Payload consists from two encapsulated modules Payload slides smoothly in the body tube Payload wiring hidden inside the modules Ejection charges need only two double wires Payload vents must align with fuselage vents

29. Part 2 Payload

31. Bacteria Journey 1. Bacteria become airborne 2. They gather on dust particles 3. Sampler collects bacteria 4. Bacteria counted 5. Data analyzed 6. Final report written

32. Flight Sequence 1.Rocket launches 2.Rocket reaches apogee 3.Drogue parachute deploys 4.Main parachute deploys 5.Above boundary layer sample (S1) 6.Below boundary layer sample (S2) 7.Near ground sample (S3) 8.Rocket lands        

33. Objectives and Success Criteria Payload Objectives Sensors record accurate atmospheric data Sensors record accurate atmospheric data Filters contain representative samples of the atmospheric bacterial levels Filters contain representative samples of the atmospheric bacterial levels Minimal contamination of bacteria samples Minimal contamination of bacteria samples Success Criteria Contrasting controls and samples Contrasting controls and samples Redundant samplers collect similar data Redundant samplers collect similar data Payload recovered undamaged Payload recovered undamaged All mechanical parts function as expected All mechanical parts function as expected Atmospheric data collected Atmospheric data collected

34. Payload Operation 1. Air enters through intake vents (grey arrows) 2. Air travels through sampler (A and B) 3. Air exits through exhaust vents (blue arrows)

35. Payload Subsystems Data Collector Pressure/Altitude Humidity Temperature Memory Bacteria Collector

36. Data Collector (AtmoGraph) Pressure/Altitude Humidity Temperature Central Processing Unit Memory Ejection Charge

37. AtmoGraph Schematic

38. Flight Computer Circuit Board 2” 6”

39. AtmoGraph (Serial # 000001)

40. AtmoGraph Parts ItemManufacturer Part Number SpecificationCost Pressure Sensor MotorolaMXPH6115A 15-115k Pa $ 9.75 Humidity Sensor HoneywellHIH403 0-100% RH $ 12.15 A/D Converter Texas Instruments ADS8341 16 bit, 100kSps $ 6.50 ProcessorParallaxP8X32A80MHz $ 11.95 ThermometerMicrochipMCP9800 -55 o C ~ 125 o C $ 1.76 MemoryMicrochip24LC1025128kB/400MHz $ 6.68 Total (each): $ 48.79

41. Boundary Layer Detection Altitude  Temperature  Boundary Layer S3S3 S2S2 S1S1 S1S1 S2S2 S3S3 Should the in-flight detection of boundary layer from temperature profile fail, fixed sampling ranges (based on the data obtained from NWS on the launch date) will be used.

42. Bacteria Collector Fan

43. Bacteria Collector Samplers Assembly

44. Bacteria Sampler HEPA Filter

45. Bacteria Sampler Servos & Plugs

46. Opening of samplers to airflow occurs when electronics control the servo, which removes the plugs and exposes the sampler to outside air ClosedOpen

47. Bacteria Collector Footprint

48. Bacteria Collector Air transport fan (and intake vent) Bacteria Sampler (with simulated HEPA filter)

49. Payload Assembly The payload electronics and batteries are located between the two bacteria collectors. Each bacteria collector has four bacteria samplers and a fan for air transport. The air enters each collector via four openings and exits via another set of four openings.

50. Sampling Progression

51. Sample Processing 1. Open payload in sterile hood 2. Pour buffer solution through HEPA filter 3. Filter buffer through fine filters 4. Stain bacteria with DAPI stain 5. Quantify bacteria using fluorescence (and measure amounts of gram- positive and gram- negative) 6. Analyze results

52. Variables and Controls Variables Independent Independent A ….. Altitude A ….. Altitude H ….. Relative Humidity H ….. Relative Humidity P ….. Atmospheric Pressure P ….. Atmospheric Pressure T ….. Temperature T ….. Temperature Dependent Dependent X ….. Bacterial Concentration X ….. Bacterial Concentration N ….. Bacterial Classification N ….. Bacterial Classification B ….. Altitude of boundary layer B ….. Altitude of boundary layer Controls Control Filter Control Filter Dual Sampling Dual Sampling Consistent staining Consistent staining Consistent counting method Consistent counting method Primary Correlation X = f (A)

53. Feasibility of Design HEPA filter collects bacteria through HEPA filter collects bacteria through Impaction Impaction Electrostatic Attraction Electrostatic Attraction Inertia of Bacteria Inertia of Bacteria HEPA filter extremely effective at high air velocity HEPA filter extremely effective at high air velocity Air fan draws sufficient amount of air Air fan draws sufficient amount of air UV hoods ensure sterility of bacteria samples UV hoods ensure sterility of bacteria samples

54. Airflow Calculations Our current payload fan meets experiment requirements of 36 cubic feet per minute Our current payload fan meets experiment requirements of 36 cubic feet per minute  x 0.5625 inches² x 1 foot² x 51 feet X 60 seconds = 1 144 in² second 1 minute 1 144 in² second 1 minute = 37.55184 ft³/minute.

55. Payload Risks RiskConsequenceMitigation Payload damage after impact Unusable data Double check parachute on ground, static testing Electronic failure Atmospheric data lost, no collection Electronics undergo extensive on-ground testing Contamination of filters before flight Unusable data Payload constructed in sterile environment. Sealed transport to launch site. Contamination of filters after flight Unusable data Placed in sterile container after flight Valves malfunctioning No / Unusable data Ground tests, new batteries and realignment before each flight.

56. Changes to Payload Entire payload shortened 16” Entire payload shortened 16” Payload E-Bay shorted 2” Payload E-Bay shorted 2” New fans have higher flow rate (37 cfm) New fans have higher flow rate (37 cfm) Sampler tubes shortened for weight and length loss Sampler tubes shortened for weight and length loss

57. Science Value Bacterial concentrations in relation to boundary layer location Provide baseline bacterial concentration Provide baseline bacterial concentration Climate affects bacterial population Climate affects bacterial population Show how bacteria respond to environment Show how bacteria respond to environment

58. Thank you! Any Questions?