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Bacteria Hunters

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

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Bacteria Hunters

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

  2. Part 1Vehicle

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

  4. Flight Sequence    • Rocket launches • Rocket reaches apogee • Drogue parachute deploys • Main parachute deploys • Above boundary layer sample (S1) • Below boundary layer sample (S2) • Near ground sample (S3) • 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 Target altitude of 5,280ft reached Payload delivered undamaged Proper deployment of all parachutes Safe recovery of the vehicle and the payload without damage

  6. Full Scale Rocket CG CP CP 98.329” (from nosetip) CG 81.908” (from nosetip) Static Margin 4.11 calibers Length 124.25” Diameter 4.0” Liftoff weight 22.5 Pounds Motor Aerotech K700W RMS

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

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

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

  15. Calculated Ejection Charges Ejection charges were verified in static testing and during the test flight. All parachutes deployed.

  16. Parachutes

  17. Verification Matrix: Components 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

  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

  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 New parachute sizes tested Ejection charge calculations tested Dual-deployment scheme tested Validity of simulation results tested Rocket stability tested

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

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

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

  27. Test Flight Results

  28. Payload Integration Flight Computer Altimeter • 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 2Payload

  30. Bacteria Journey Bacteria become airborne They gather on dust particles Sampler collects bacteria Bacteria counted Data analyzed Final report written

  31. Flight Sequence    • Rocket launches • Rocket reaches apogee • Drogue parachute deploys • Main parachute deploys • Above boundary layer sample (S1) • Below boundary layer sample (S2) • Near ground sample (S3) • Rocket lands     

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

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

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

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

  36. AtmoGraph Schematic

  37. Flight Computer Circuit Board 2” 6”

  38. AtmoGraph (Serial # 000001)

  39. AtmoGraph Parts

  40. Boundary Layer Detection Boundary Layer Temperature S1 S2 S3 S3 S2 S1 Altitude 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.

  41. Bacteria Collector Fan

  42. Bacteria Collector SamplersAssembly

  43. Bacteria SamplerHEPA Filter

  44. Bacteria SamplerServos & Plugs

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

  46. Bacteria Collector Footprint

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

  48. 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.

  49. Sampling Progression

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