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Bacteria Hunters

Bacteria Hunters. Bacterial Concentrations Above and Below the Planetary Boundary Layer. Part 1 Vehicle. Major Milestones Schedule. February 15 th Full scale model complete February 21 th First full scale launch March 15 th Payload complete March 18 th FRR due

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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 February 15th Full scale model complete February 21th First full scale launch March 15th Payload complete March 18th FRR due March 21st Second full scale launch March 28th All-Systems-Ready for SLI launch April 3rd 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 CP 114.6” (from nosetip) CG 88.6” (from nosetip) Static Margin 6.5 calibers Length 139.3” Diameter 4.0” Liftoff weight 22.8 Pounds Motor Aerotech K700W RMS

  7. Rocket Schematics Booster Bacteria Collector #2 Bacteria Collector #1 and Main Parachute E-Bay Drogue Parachute Nosecone

  8. 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

  9. Thrust Profile for K700W

  10. Acceleration Profile for K700W

  11. Altitude Profile for K700W

  12. Flight Safety Parameters Stability static margin: 6.5 Thrust to weight ratio: 8.3 Velocity at launch guide departure: 45.2mph

  13. 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 ]

  14. Calculated Ejection Charges Ejection charges will be verified in static testing when the full scale model is constructed.

  15. Parachutes

  16. 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

  17. 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.

  18. Verification Matrix

  19. Scale Model Launch

  20. Scale Model Flight Objectives Test dual deployment avionics Test full deployment scheme Test ejection charge calculations Test payload integration (partially) Test validity of simulation results Test rocket stability

  21. 2/3 Scale Model Parameters Liftoff Weight: 5.846 pounds Motor: AT-RMS I357T Length: 90.925” Diameter: 2.6” Stability Margin: 8.9 calibers

  22. Scale Model Flight 1 2 3 4 5 WIND Rocket lifts off from rail, weather cocking to the right. Wind comes from the right, rocket turns into the wind. Rocket goes into a corkscrew. Rocket corrects to the left. Motor burnout. 6 7 8 9 10 Rocket coasts into the wind COAST

  23. Scale Model Flight Results Apogee: 1158 ft Rocksim prediction: 2093 feet Time to apogee: 7.95 s Drogue parachute: at apogee Main parachute: 288 ft, 21.7s

  24. Scale Model Flight Data RockSim prediction Apogee Main parachute deployment (separation)

  25. Scale Model Flight Results

  26. Scale Model Flight Conclusions • Observations • Excessive altitude loss due to weathercocking/corkscrew • Construction method sufficiently robust • Dual deployment avionics (PerfectFlite MAWD) works • Lack of detailed checklist the cause for separation • Ejection charge calculations correct • Suggestions for improvement • Always use a full checklist • Launch the scale model again to investigate further • Implement spin stabilization using airfoiled fins

  27. 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

  28. Part 2Payload

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

  30. 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     

  31. 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

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

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

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

  35. 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.

  36. AtmoGraph Parts

  37. Bacteria Collector Fan

  38. Bacteria SamplerHEPA Filter

  39. Bacteria SamplerServos & Plugs

  40. Bacteria Collector Footprint

  41. Bacteria Collector Mockup Air fan Battery Filters Computer Plug Plug

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

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

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

  45. Payload Risks

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

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