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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 - PowerPoint PPT Presentation


  • Bacteria HuntersBacterial Concentrations Above and Below the Planetary Boundary Layer

  • Part 1Vehicle

  • Major Milestones ScheduleFebruary 15th Full scale model completeFebruary 21th First full scale launchMarch 15th Payload completeMarch 18th FRR dueMarch 21stSecond full scale launchMarch 28th All-Systems-Ready for SLI launchApril 3rd FRR presentationApril 19thSLI launchMay 10th Payload analysis completeMay 22ndPLAR due

  • Flight SequenceRocket launchesRocket reaches apogeeDrogue parachute deploysMain parachute deploysAbove 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.

  • Success CriteriaStable flight of the vehicleTarget altitude of 5,280ft reachedPayload delivered undamaged Proper deployment of all parachutesSafe recovery of the vehicle and the payload without damage

  • Full Scale RocketCP114.6 (from nosetip)CG88.6 (from nosetip)Static Margin6.5 calibersLength139.3Diameter4.0Liftoff weight22.8 PoundsMotorAerotech K700W RMS

  • Rocket SchematicsBoosterBacteria Collector #2Bacteria Collector #1 and Main ParachuteE-BayDrogue ParachuteNosecone

  • Construction MaterialsFins: 1/8 balsa between 1/32 G10 fiberglassBody: fiberglass tubing, fiberglass couplersBulkheads: 1/2 plywoodMotor Mount: 54mm phenolic tubing, 1/2 plywood centering ringsNosecone: commercially made plastic noseconeRail Buttons: standard size nylon buttonsMotor Retention System: Aeropack screw-on motor retainerAnchors: 1/4 stainless steel U-BoltsEpoxy: West System with appropriate fillers

  • Thrust Profile for K700W

  • Acceleration Profile for K700W

  • Altitude Profile for K700W

  • Flight Safety ParametersStability static margin: 6.5

    Thrust to weight ratio: 8.3

    Velocity at launch guidedeparture: 45.2mph

  • Ejection Charge CalculationsW = 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 ]

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

    ParachuteEjection charge(FFFF black powder)Main Parachute2.5 gramDrogue Parachute2.0 gram

  • Parachutes

    ParachuteWeight[lbs]Diameter[in]Descent weight[lbs]DescentRate[fps]Drogue0.101618.371Main0.407218.315

  • Verification Matrix: ComponentsTested components:

    C1: Body (including construction techniques)C2: AltimeterC3: Data Acquisition System (custom computer board and sensors)C4: ParachutesC5: FinsC6: PayloadC7: Ejection chargesC8: Launch systemC9: Motor mountC10: Screamers, beaconsC11: Shock cords and anchorsC12: Rocket stability

  • Verification Matrix: TestsVerification 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 durabilityV4 Prototype Flight: testing the feasibility of the vehicle with a scale model.V5 Functionality Test: test of basic functionality of a device on the groundV6 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


  • Scale Model Launch

  • Scale Model Flight ObjectivesTest dual deployment avionicsTest full deployment schemeTest ejection charge calculationsTest payload integration (partially)Test validity of simulation resultsTest rocket stability

  • 2/3 Scale Model ParametersLiftoff Weight: 5.846 poundsMotor: AT-RMS I357TLength: 90.925 Diameter: 2.6 Stability Margin: 8.9 calibers

  • Scale Model FlightRocket lifts off from rail, weather cocking to the right.WINDWind comes from the right, rocket turns into the wind.Rocket goes intoa corkscrew.

    Rocket corrects to the left.

    Motor burnout.

    Rocket coasts into the wind


  • Scale Model Flight ResultsApogee: 1158 ftRocksim prediction: 2093 feetTime to apogee: 7.95 sDrogue parachute: at apogeeMain parachute: 288 ft, 21.7s

  • Scale Model Flight DataApogeeMain parachutedeployment (separation)RockSim prediction

  • Scale Model Flight Results

    DescriptionStart timeand startaltitudeEnd time and endaltitude Descent rateVehicle underdrogue8s1150ft22s275ft62.5 fpsVehicle undermainSeparation(no applicable data)

  • Scale Model Flight ConclusionsObservations

    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 2Payload

  • Bacteria JourneyBacteria become airborneThey gather on dust particlesSampler collects bacteriaBacteria countedData analyzedFinal report written

  • Flight SequenceRocket launchesRocket reaches apogeeDrogue parachute deploysMain parachute deploysAbove boundary layer sample (S1)Below boundary layer sample (S2)Near ground sample (S3)Rocket lands

  • Objectives and Success CriteriaPayload ObjectivesSensors record accurate atmospheric dataFilters contain representative samples of the atmospheric bacterial levelsMinimal contamination of bacteria samples

    Success CriteriaContrasting controls and samplesRedundant samplers collect similar dataPayload recovered undamagedAll mechanical parts function as expectedAtmospheric data collected

  • Payload OperationAir enters through intake vents (grey arrows)

    Air travels through sampler (A and B)

    Air exits through exhaust vents (blue arrows)

  • Payload SubsystemsData CollectorPressure/AltitudeHumidityTemperatureMemoryBacteria Collector

  • Data Collector (AtmoGraph)Pressure/AltitudeHumidityTemperatureCentral Processing UnitMemoryEjection Charge

  • Boundary Layer DetectionAltitude Temperature Boundary LayerS3S2S1S1S2S3Should 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

  • Bacteria CollectorFan

  • Bacteria Sampler HEPA Filter

  • Bacteria Sampler Servos & Plugs

  • Bacteria Collector Footprint

  • Bacteria Collector MockupAir fanBatteryComputerFiltersPlugPlug

  • Sample ProcessingOpen payload in sterile hoodPour buffer solution through HEPA filterFilter buffer through fine filtersStain bacteria with DAPI stainQuantify bacteria using fluorescence (and measure amounts of gram-positive and gram-negative)Analyze results

  • Variables and ControlsVariablesIndependentA .. AltitudeH .. Relative HumidityP .. Atmospheric PressureT .. TemperatureDependentX .. Bacterial ConcentrationN .. Bacterial ClassificationB .. Altitude of boundary layer

    ControlsControl FilterDual SamplingConsistent stainingConsistent counting methodPrimary CorrelationX = f (A)

  • Feasibility of DesignHEPA filter collects bacteria throughImpactionElectrostatic AttractionInertia of BacteriaHEPA filter extremely effective at high air velocityAir fan draws sufficient amount of airUV hoods ensure sterility of bacteria samples

  • Payload Risks

  • Science ValueBacterial concentrations in relation to boundary layer location

    Provide baseline bacterial concentrationClimate affects bacterial populationShow how bacteria respond to environment

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