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 March 21 st Second full scale launch March 28 th All-Systems-Ready for SLI launch April 3 rd FRR presentation April 19 th SLI launch May 10 th Payload analysis complete May 22 nd PLAR due

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.        

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

Full Scale Rocket CP114.6” (from nosetip) CG88.6” (from nosetip) Static Margin6.5 calibers Length139.3” Diameter4.0” Liftoff weight22.8 Pounds MotorAerotech K700W RMS

Rocket Schematics 1. Booster 2. Bacteria Collector #2 3. Bacteria Collector #1 and Main Parachute 4. E-Bay 5. Drogue Parachute 6. Nosecone

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

Thrust Profile for K700W

Acceleration Profile for K700W

Altitude Profile for K700W

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

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, [ ft-lb o R -1 lb-mol -1 ] R = combustion gas constant, [ 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 ]

Calculated Ejection Charges Parachute Ejection charge (FFFF black powder) Main Parachute 2.5 gram Drogue Parachute 2.0 gram Ejection charges will be verified in static testing when the full scale model is constructed.

ParachutesParachuteWeight[lbs]Diameter[in] Descent weight [lbs]DescentRate[fps] Drogue Main

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

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.

Verification Matrix V 1 V 2 V 3 V 4 V 5 V 6 V 7 V 8 V 9 V 10 C 1 PFFP C 2 FFFFF C 3 PPPP C 4 FFF C 5 PF C 6 PP C 7 FFFFPP C 8 FP C 9 PF C 10 P C 11 PPPFF C 12 FF

Scale Model Launch

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

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

Scale Model Flight Rocket lifts off from rail, weather cocking to the right. WIND Wind comes from the right, rocket turns into the wind. Rocket goes into a corkscrew. Rocket corrects to the left. Motor burnout. Rocket coasts into the wind COAST

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

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

Scale Model Flight Results Description Start time and start altitude End time and end altitude Descent rate Vehicle under drogue 8s 1150ft 22s 275ft 62.5 fps Vehicle under main Separation (no applicable data)

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

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

Part 2 Payload

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

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        

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

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)

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

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

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.

AtmoGraph Parts ItemManufacturer Part Number SpecificationCost Pressure Sensor MotorolaMXPH6115A k Pa $ 9.75 Humidity Sensor HoneywellHIH % RH $ A/D Converter Texas Instruments ADS bit, 100kSps $ 6.50 ProcessorParallaxP8X32A80MHz $ ThermometerMicrochipMCP o C ~ 125 o C $ 1.76 MemoryMicrochip24LC kB/400MHz $ 6.68 Total (each): $ 48.79

Bacteria Collector Fan

Bacteria Sampler HEPA Filter

Bacteria Sampler Servos & Plugs

Bacteria Collector Footprint

Bacteria Collector Mockup Air fan Battery Computer Filters Plug

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

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)

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

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.

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