Bacteria HuntersBacteria HuntersBacterial Concentrations Above Bacterial Concentrations Above

and Below the Planetary and Below the Planetary Boundary LayerBoundary Layer

Part 1Part 1VehicleVehicle

Major Milestones Major Milestones ScheduleSchedule

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

Flight Flight SequenceSequence

1. Rocket launches2. Rocket reaches apogee3. Drogue parachute deploys4. Main parachute deploys5. Above boundary layer sample (S1)6. Below boundary layer sample (S2)7. Near ground sample (S3)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 CriteriaSuccess Criteria

Stable flight of the vehicleStable flight of the vehicle

Target altitude of 5,280ft reachedTarget altitude of 5,280ft reached

Payload delivered undamaged Payload delivered undamaged

Proper deployment of all parachutesProper deployment of all parachutes

Safe recovery of the vehicle and the Safe recovery of the vehicle and the

payload without damagepayload without damage

Full Scale RocketFull 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 PoundsMotor Aerotech K700W RMS

Rocket SchematicsRocket Schematics

1.1. BoosterBooster2.2. Bacteria Collector #2Bacteria Collector #23.3. Bacteria Collector #1 and Main Bacteria Collector #1 and Main

ParachuteParachute4.4. E-BayE-Bay5.5. Drogue ParachuteDrogue Parachute6.6. NoseconeNosecone

Construction MaterialsConstruction Materials Fins:Fins: 1/8” balsa between 1/32” G10 fiberglass 1/8” balsa between 1/32” G10 fiberglass Body:Body: fiberglass tubing, fiberglass couplers fiberglass tubing, fiberglass couplers Bulkheads:Bulkheads: 1/2” plywood 1/2” plywood Motor Mount:Motor Mount: 54mm phenolic tubing, 1/2” plywood 54mm phenolic tubing, 1/2” plywood

centering ringscentering rings Nosecone:Nosecone: commercially made plastic nosecone commercially made plastic nosecone Rail Buttons:Rail Buttons: standard size nylon buttons standard size nylon buttons Motor Retention System:Motor Retention System: Aeropack screw-on motor Aeropack screw-on motor

retainerretainer Anchors:Anchors: 1/4” stainless steel U-Bolts 1/4” stainless steel U-Bolts Epoxy:Epoxy: West System with appropriate fillers West System with appropriate fillers

Thrust Profile for K700WThrust Profile for K700W

Acceleration Profile for Acceleration Profile for K700WK700W

Burnout

0.0

2.5

5.0

7.5

10.0

12.5

0 1 2 3 4 5 6 7 8 9 10

Bacteria HunterLaunched with [K700W-*]

y - A

ccel

erat

ion

Gee

's

Time

Altitude Profile for Altitude Profile for K700WK700W

ApogeeBurnoutP: Drogue deployment

P: Parachute deployment

0

1000

2000

3000

4000

5000

6000

7000

0 25 50 75 100 125 150 175 200

Bacteria HunterLaunched with [K700W-None]

Alti

tude

Fee

t

Time

Flight Safety ParametersFlight Safety Parameters

Stability static margin:Stability static margin: 6.56.5

Thrust to weight ratio:Thrust to weight ratio: 8.38.3

Velocity at launch guideVelocity at launch guide

departure:departure: 45.245.2mphmph

Ejection Charge Ejection Charge CalculationsCalculations

W = dP * V/(R * T)W = dP * V/(R * T)

Where: Where:

dPdP = ejection charge pressure, 15 [ = ejection charge pressure, 15 [ psi psi ]]

RR = combustion gas constant, 22.16 [ = combustion gas constant, 22.16 [ft-lb ft-lb ooRR-1-1 lb-mol lb-mol-1-1 ]]

TT = combustion gas temperature, 3307 [ = combustion gas temperature, 3307 [ ooR R ]]

VV = free volume [ = free volume [ in in 3 3 ]]

WW = ejection charge weight [ = ejection charge weight [ lbs lbs ]]

Calculated Ejection Calculated Ejection ChargesCharges

ParachuteParachute Ejection chargeEjection charge

(FFFF black powder)(FFFF black powder)

Main ParachuteMain Parachute 2.5 gram2.5 gram

Drogue ParachuteDrogue Parachute 2.0 gram2.0 gram

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

ParachutesParachutes

ParachuteParachuteWeightWeight

[lbs][lbs]

DiameterDiameter

[in][in]

Descent Descent weightweight

[lbs][lbs]

DescentDescent

RateRate

[fps][fps]

DrogueDrogue 0.100.10 1616 18.318.3 7171

MainMain 0.400.40 7272 18.318.3 15 15

Verification Matrix: Verification Matrix: ComponentsComponents

Tested components:Tested components:

C1:C1: Body (including construction techniques) Body (including construction techniques) C2:C2: Altimeter Altimeter C3:C3: Data Acquisition System (custom computer board and Data Acquisition System (custom computer board and

sensors)sensors) C4:C4: Parachutes Parachutes C5:C5: Fins Fins C6:C6: Payload Payload C7:C7: Ejection charges Ejection charges C8:C8: Launch system Launch system C9:C9: Motor mount Motor mount C10:C10: Screamers, beacons Screamers, beacons C11:C11: Shock cords and anchors Shock cords and anchors C12:C12: Rocket stability Rocket stability

Verification Matrix: Verification Matrix: TestsTests

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 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 MatrixVerification MatrixV V

11 V V 2 2 V V

33 V V 4 4 V V

55 V V 66 V V

77 V V 88 V V

99 V V 1010

C C 11 PP FF FF PP

C C 22 FF FF FF FF FF

C C 33 PP PP PP PP

C C 44 FF FF FF

C C 55 PP FF

C C 66 PP PP

C C 77 FF FF FF FF PP PP

C C 88 FF PP

C C 99 PP FF

C C 1010 PP

C C 1111 PP PP PP FF FF

C C 1212 FF FF

Scale Model LaunchScale Model Launch

Scale Model Flight Scale Model Flight ObjectivesObjectives

Test dual deployment avionicsTest dual deployment avionics Test full deployment schemeTest full deployment scheme Test ejection charge calculationsTest ejection charge calculations Test payload integration (partially)Test payload integration (partially) Test validity of simulation resultsTest validity of simulation results Test rocket stabilityTest rocket stability

2/3 Scale Model 2/3 Scale Model ParametersParameters

Liftoff Weight:Liftoff Weight: 5.846 pounds5.846 pounds Motor:Motor: AT-RMS AT-RMS

I357TI357T Length:Length: 90.925” 90.925” Diameter:Diameter: 2.6” 2.6” Stability Margin:Stability Margin: 8.9 calibers8.9 calibers

Scale Model FlightScale 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 intoa corkscrew.

Rocket corrects to the left.

Motor burnout.

Rocket coasts into the wind COAST

1 2 3 4 5

6 7 8 9 10

Scale Model Flight Scale Model Flight ResultsResults

Apogee:Apogee: 1158 1158 ftft Rocksim prediction: 2093 feetRocksim prediction: 2093 feet

Time to apogee:Time to apogee: 7.95 7.95 ss Drogue parachute:Drogue parachute: at apogee at apogee Main parachute:Main parachute: 288 288 ftft, ,

21.721.7ss

Scale Model Flight DataScale Model Flight Data

Apogee

Main parachutedeployment (separation)

RockSim prediction

Scale Model Flight Scale Model Flight ResultsResults

DescriptionDescription Start timeStart time

and startand start

altitudealtitude

End time End time and endand end

altitude altitude

Descent Descent raterate

Vehicle Vehicle underunder

droguedrogue

88ss

11501150ftft

2222ss

275275ftft62.5 62.5 fpsfps

Vehicle Vehicle underunder

mainmain

SeparationSeparation

(no applicable data)(no applicable data)

Scale Model Flight Scale Model Flight ConclusionsConclusions

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 integrationPayload 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 2Part 2PayloadPayload

Bacteria Bacteria JourneyJourney

1.1. Bacteria become Bacteria become airborneairborne

2.2. They gather on They gather on dust particlesdust particles

3.3. Sampler collects Sampler collects bacteriabacteria

4.4. Bacteria countedBacteria counted

5.5. Data analyzedData analyzed

6.6. Final report Final report writtenwritten

Flight Flight SequenceSequence

1. Rocket launches2. Rocket reaches apogee3. Drogue parachute deploys4. Main parachute deploys5. Above boundary layer sample (S1)6. Below boundary layer sample (S2)7. Near ground sample (S3)8. Rocket lands

Objectives and Success Objectives and Success CriteriaCriteria

Payload ObjectivesPayload Objectives

Sensors record Sensors record accurate atmospheric accurate atmospheric datadata

Filters contain Filters contain representative samples representative samples of the atmospheric of the atmospheric bacterial levelsbacterial levels

Minimal contamination Minimal contamination of bacteria samplesof bacteria samples

Success CriteriaSuccess Criteria

Contrasting controls and Contrasting controls and samplessamples

Redundant samplers Redundant samplers collect similar datacollect similar data

Payload recovered Payload recovered undamagedundamaged

All mechanical parts All mechanical parts function as expectedfunction as expected

Atmospheric data Atmospheric data collectedcollected

Payload Payload OperatioOperationn

1.1. Air enters through Air enters through intake vents intake vents (grey (grey arrows)arrows)

2.2. Air travels Air travels through sampler through sampler (A and B)(A and B)

3.3. Air exits through Air exits through exhaust vents exhaust vents (blue arrows)(blue arrows)

Payload SubsystemsPayload Subsystems

Data Collector

Pressure/Altitude

Humidity

Temperature

Memory

Bacteria Collector

Data Collector Data Collector (AtmoGraph)(AtmoGraph)

Pressure/Altitude

Humidity

Temperature Central Processing Unit

Memory

Ejection Charge

Boundary Layer Boundary Layer DetectionDetection

Altitude

Tem

pera

ture

Boundary Layer

S3 S2 S1

S1

S2

S3

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 PartsAtmoGraph Parts

ItemItem ManufacturManufacturerer

Part Part NumberNumber

SpecificatioSpecificationn

CostCost

Pressure Pressure SensorSensor MotorolaMotorola MXPH6115AMXPH6115A 15-115k Pa15-115k Pa $ 9.75$ 9.75

Humidity Humidity SensorSensor HoneywellHoneywell HIH403HIH403 0-100% RH0-100% RH $ 12.15$ 12.15

A/D A/D ConverterConverter

Texas Texas InstrumentsInstruments ADS8341ADS8341 16 bit, 16 bit,

100kSps100kSps $ 6.50$ 6.50

ProcessorProcessor ParallaxParallax P8X32AP8X32A 80MHz80MHz $ 11.95$ 11.95

ThermometerThermometer MicrochipMicrochip MCP9800MCP9800 -55-55ooC ~ C ~ 125125ooCC

$ 1.76$ 1.76

MemoryMemory MicrochipMicrochip 24LC102524LC1025 128kB/128kB/400MHz400MHz $ 6.68$ 6.68

Total (each):Total (each): $ 48.79$ 48.79

Bacteria CollectorBacteria Collector

Fan

Bacteria SamplerBacteria Sampler HEPA FilterHEPA Filter

Bacteria SamplerBacteria Sampler Servos & PlugsServos & Plugs

Bacteria Collector Bacteria Collector FootprintFootprint

Bacteria Collector Bacteria Collector MockupMockup

Air fan

Battery

Computer

Filters

PlugPlug

Sample Sample ProcessinProcessingg

1.1. Open payload in Open payload in sterile hoodsterile hood

2.2. Pour buffer Pour buffer solution through solution through HEPA filterHEPA filter

3.3. Filter buffer Filter buffer through fine filtersthrough fine filters

4.4. Stain bacteria with Stain bacteria with DAPI stainDAPI stain

5.5. Quantify bacteria Quantify bacteria using fluorescence using fluorescence (and measure (and measure amounts of gram-amounts of gram-positive and gram-positive and gram-negative)negative)

6.6. Analyze resultsAnalyze results

Variables and ControlsVariables and Controls

VariablesVariables

IndependentIndependent AA ….. Altitude ….. Altitude HH ….. Relative Humidity ….. Relative Humidity PP ….. Atmospheric Pressure ….. Atmospheric Pressure T ….. T ….. TemperatureTemperature

DependentDependent XX ….. Bacterial ….. Bacterial

ConcentrationConcentration NN ….. Bacterial Classification ….. Bacterial Classification BB ….. Altitude of boundary layer ….. Altitude of boundary layer

ControlsControls

Control FilterControl Filter Dual SamplingDual Sampling Consistent stainingConsistent staining Consistent counting Consistent counting

methodmethod

Primary Correlation

X = f (A)

Feasibility of DesignFeasibility of Design

HEPA filter collects bacteria throughHEPA filter collects bacteria through ImpactionImpaction Electrostatic AttractionElectrostatic Attraction Inertia of BacteriaInertia of Bacteria

HEPA filter extremely effective at high air HEPA filter extremely effective at high air velocityvelocity

Air fan draws sufficient amount of airAir fan draws sufficient amount of air UV hoods ensure sterility of bacteria UV hoods ensure sterility of bacteria

samplessamples

Payload RisksPayload RisksRiskRisk ConsequenceConsequence MitigationMitigation

Payload damage Payload damage after impactafter impact

Unusable dataUnusable data Double check Double check parachute on parachute on ground, static ground, static testingtesting

Electronic failureElectronic failure Atmospheric data Atmospheric data lost, no collectionlost, no collection

Electronics undergo Electronics undergo extensive on-extensive on-ground testingground testing

Contamination of Contamination of filters before flightfilters before flight

Unusable dataUnusable data Payload constructed Payload constructed in sterile in sterile environment. environment. Sealed transport to Sealed transport to launch site.launch site.

Contamination of Contamination of filters after flightfilters after flight

Unusable dataUnusable data Placed in sterile Placed in sterile container after container after flightflight

Valves Valves malfunctioningmalfunctioning

No / Unusable dataNo / Unusable data Ground tests, new Ground tests, new batteries and batteries and realignment before realignment before each flight.each flight.

Science ValueScience Value

Bacterial concentrations in relation Bacterial concentrations in relation to boundary layer locationto boundary layer location

Provide baseline bacterial Provide baseline bacterial concentrationconcentration

Climate affects bacterial populationClimate affects bacterial population Show how bacteria respond to Show how bacteria respond to

environmentenvironment