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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 - PowerPoint PPT Presentation

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  • Bacteria HuntersBacterial Concentrations Above and Below the Planetary Boundary Layer

  • Part 1Vehicle

  • Major Milestones ScheduleMarch 21stSecond full scale launchMarch 22ndPayload completion and testingMarch 28th All-Systems-Ready for SLI launchApril 2nd 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 RocketCP98.329 (from nosetip)CG81.908 (from nosetip)Static Margin4.11 calibersLength124.25Diameter4.0Liftoff weight22.5 PoundsMotorAerotech K700W RMSCGCP

  • 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

  • Motor RetentionAeropack Tailcone Motor Retainer

  • Thrust Profile for K700W

  • Acceleration Profile for K700W

  • Altitude Profile for K700W

  • Projected DriftMain deployment AltitudeWind speed

    mph52805000400030002000100090000.0 ft0.0 ft0.0 ft0.0 ft0.0 ft0.0 ft0.0 ft53,097 ft2,960 ft2,470 ft1,918 ft1,491 ft1,001 ft952 ft106,195 ft5,921 ft4,941 ft3,962 ft2,983 ft2,003 ft1,905 ft159,292 ft8,881 ft7,412 ft5,943 ft4,474 ft3,005 ft2,858 ft2012,390 ft11,842 ft9,883 ft7,924 ft5,966 ft4,007 ft3,811 ft

  • Flight Safety ParametersStability static margin: 4.11

    Thrust to weight ratio: 6.85

    Velocity at launch guidedeparture: 84.6fps

  • 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 were verified in static testing and during the test flight. All parachutes deployed.

    ParachuteEjection charge(FFFF black powder)Main Parachute60 grains(3.89 grams)Drogue Parachute35 grains(2.27 grams)

  • Parachutes

    ParachuteDiameter[in]Descent weight[lbs]DescentRate[fps]Drogue1620.1575.6Main8420.15 12.5

  • 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

    V 1V 2 V 3V 4 V 5 V 6 V 7V 8 V 9V 10C 1FFFFC 2FFFFFC 3PPPPC 4FFFC 5FFC 6PPC 7FFFFFFC 8FFC 9FFC 10FC 11FFFFFC 12FF

  • Test Flights Results

  • Full Scale Vehicle Test Flight

  • First Full-Scale Vehicle Launch ConclusionsObservations

    The rocket flew to a height of 1586 ftThe 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

  • Second Full Scale Vehicle Flight Objectives MetModified vehicle design testedNew parachute sizes testedEjection charge calculations testedDual-deployment scheme testedValidity of simulation results testedRocket stability tested

  • Full Scale Model Parameters(after modifications)Liftoff Weight: 24.00 poundsMotor: Aerotech K700WLength: 10.35 ftDiameter: 4Stability Margin: 4.11 calibers

  • Test Flight #2 ResultsApogee: 5071ftRocksim prediction: 4800 feet

    Time to apogee: 17.15s

    Drogue parachute: apogee at 17.15 s

    Main parachute: 900ft, 72.3s

  • Test Flight DataApogee (drogue deployment)Main parachutedeployment

  • Test Flight Results

    DescriptionStart timeand startaltitudeEnd time and endaltitude Descent rateVehicle underdrogue17.15 s5071ft72.3s900ft75.6 fpsVehicle under main72.3s900 ft144.2s0 ft12.5 fps

  • 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

  • AtmoGraph Schematic

  • Flight Computer Circuit Board26

  • AtmoGraph (Serial # 000001)

  • AtmoGraph Parts

    ItemManufacturerPart NumberSpecificationCostPressure SensorMotorolaMXPH6115A15-115k Pa$ 9.75Humidity SensorHoneywellHIH4030-100% RH$ 12.15A/D ConverterTexas InstrumentsADS834116 bit, 100kSps$ 6.50ProcessorParallaxP8X32A80MHz$ 11.95ThermometerMicrochipMCP9800-55oC ~ 125oC$ 1.76MemoryMicrochip24LC1025128kB/400MHz$ 6.68Total (each):$ 48.79

  • 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.

  • Bacteria CollectorFan

  • Bacteria Collector SamplersAssembly

  • Bacteria Sampler HEPA Filter

  • Bacteria Sampler Servos & Plugs

  • Opening of samplers to airflow occurs when electronics control the servo, which removes the plugs and exposes the sampler to outside airClosedOpen

  • Bacteria Collector Footprint

  • Bacteria CollectorAir transport fan(and intake vent)Bacteria Sampler(with simulated HEPAfilter)

  • Payload AssemblyThe 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.

  • Sampling Progression

  • 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