Preliminary Design Review Presentation 2012-2013 NASA USLI

1Preliminary Design Review PresentationTarleton State UniversityNASA USLI 2012-20131Presentation Outline#Title3467891011121314151617181920222324252627

Team IntroductionMission SummaryVehicle DimensionsVehicle SectionsElliptical Nose ConeBallast SystemUpper Body AirframePayload Housing StructureBooster SectionFinsStatic Stability MarginVehicle Safety Verification and TestingMotor Trade and SelectionMotor Selection12:1 Thrust to Weight RatioVehicle Verification and TestingRecovery Verification and TestingDual Deployment Avionics BaysDeployment Altimeters SelectionDeployment Altimeters WiringMaximum Landing VelocityCalculating Minimum Diameter of Main Parachute2829303132333435363739404142434445464849505152Main Parachute SelectionDrift for Main ParachuteMaximum Drift for DrogueMinimum Drogue Parachute DiameterDrogue Parachute SelectionDeployment Altimeters WiringRecovery ComponentsKinetic EnergyWeather CockingLanding RadiusSMD PayloadPayload FrameworkAtmospheric Data GatheringPrecision of InstrumentationAutonomous Camera OrientationPayload PCB SchematicScoring Altimeter SelectionPayload Verification and TestingCost of Vehicle and PayloadBudget SummaryEducational OutreachProject OutlineSMD Deliverable Schedule2Discuss how many members, fields of studies, and classificationsExpress the teams diversity: for ie. Freshman-seniors, graduate students with degrees in xxx, prior military, NAR certifications ect.2Team Introduction

33Mission SummaryScience Mission Directorate PayloadVehicleRecovery

44Vehicle Overview55Vehicle Dimensions108 inches total length5.525 inch outer diameter33.5 pounds

6Why were these dimensions choosen6Vehicle sections

Nose ConeUpper Body AirframePayload HousingBooster Section77Elliptical Nose ConeDimensions13 inch long total5.5 inch shoulderMaterialFiberglass

8Justification: Because we are operating at subsonic speeds, this was a suitable choice. We have found that elliptical noses cones create the least amount of drag while still being commercially available.8Ballast SystemWashersBulkheadsApogee Altitude Control

99Upper Body AirframeDimensions28 inches long0.075 inches thickMaterialFiberglass

10Justification: fiberglass is industry standard for its lightweight and durabilityFunctions to connect the nose cone to the payload section, houses the main parachute, altimeter bay, GPS 10Payload Housing StructureDimensions36 inches long0.125 inches thickMaterialClear Acrylic

11Functions to connect the upper body airframe to the booster section as well as house the payloadIt was selected primarily to allow the payload to remain within the flight vehicle since the camera, irradiance, and radiation sensors will be able to operate without being externally exposed, thus preventing the need to eject the payload. This reduces risks of a possible failure with a staged ejection, need for a secondary recovery, and prevents any safety issues surrounding a falling object.

11Booster SectionDimensions36 inches long0.075 inches thickMaterialsFiberglass

12Justification: Functions to house the motor retainer and motor, as well as the drogue parachute, drogue altimeter bay, GPS

12Fins

DimensionRoot Chord

12 in

Tip Chord

0 inches

Height

5 inches

Sweep Length

9.8 inches

Sweep Angle

63 Degrees

1313Static Stability margin

14Center of Gravity65.667 inches from the tip of the noseCenter of Pressure79.738 inches from the tip of the noseStability margin14.071 inches or 2.55 calibers of body width

NOTE: stability margin should be at least two calibers of body diameter.

14Vehicle Safety Verification and Testing15Structure TestingLab PrototypingLow Altitude FlightsDual Deployment TestingForce of Impact TestingFull Scale FlightsTimed Assemblies15Motor Trade and SelectionMotorApogee (ft.)Velocity Off Rail (ft./s)Total ImpulseMax. Velocity (ft./s)Average Thrust Burn Time (s)Thrust to Weight RatioAvailability/CostCesaroni L1720-WT-P534576831 lbfs3696 Ns738394 lbf1754 N2.1511.8High/$171Aerotech L1390G561866887 lbfs 3949 Ns723309 lbf 1374 N2.659.2Medium/$210Cesaroni L1090SS-P6479771082 lbfs4815 Ns733247 lbf1097 N4.47.4Medium/$3471616Motor SelectionCesaroni L1720-WT-PRail Exit Velocity 76 ft/s2.95 inch diameterTotal impulse of 831 lbf -sEstimated apogee at 5345 ft unballasted738 ft/s max velocity2.15 second burn time

17Talk about the justificationConsidered17

12:1 Thrust to Weight Ratio1818Vehicle Verification and TestingSOW#Vehicle RequirementSatisfying Design FeatureVerification Method1.1Deliver payload to 5,280 feet AGLMotor selectionTesting, Simulation1.2Carry official scoring barometric altimeterAdept A1E is included in the payload housingInspection1.3Launch vehicle remains subsonicMotor selectionTesting, Analysis1.4Vehicle must be recoverable and reusableRecovery system allows a safe landing of vehicleTesting, Inspection, Analysis1.5Vehicle has a maximum of four sectionsVehicle is composed of 3 tethered sectionsInspection1.6Vehicle prepared for flight within 2 hoursLaunch operations and assembly procedureTesting, Inspection1.7Launch-ready for a minimum of one hourCritical on-board components run for 1.5 hoursTesting, Inspection, Analysis1.8Vehicle compatible with 8 feet long 1 inch rail1010 rail buttons attached to vehicle bodyInspection1.9Launch vehicle use 12 volt DC firing systemMotor is compatible with firing systemInspection1.11Commercially available, certified APCP motorMotor Selection: Cesaroni L1720Inspection1.12Total impulse under 5,120 Ns3695.6 NsInspection1.15Final vehicle successfully launched and recovered prior to FRRTesting ScheduleTesting1919Recovery2020Recovery Verification and TestingSOW#Recovery System RequirementSatisfying Design FeatureVerification Method2.1Dual Deployment RecoveryAltimeters fire at the prescribed altitudesTesting2.2Maximum KE of 75 ft-lbf.Main parachute selectionTesting, Analysis2.32500ft Landing RadiusDrogue and main parachute selectionTesting, Analysis2.4Independent Recovery ElectronicsAltimeters have dedicated Power SuppliesInspection2.5Redundant AltimetersDeployment by main and backup altimeterInspection2.6External Arming SwitchesPort holes in vehicle airframe to altimeter baysInspection2.7Each altimeter have a dedicated power supplyEach altimeter uses a separate 9 Volt batteryInspection2.8Arming switches able to be locked ONPort holes in vehicle airframe to altimeter baysTesting, Inspection2.9Arming switches located max of 6ft from baseMain altimeter bay is located at 5 8Inspection2. 10Use removable shear pinsNylon shear pins couple parachute compartmentsInspection2.11Vehicle carry an electronic tracking deviceGPS in payload and altimeter baysTesting2.12Recovery electronics not disrupted by other electronicsAltimeters shielded by copper mesh liningInspection, Testing2.12.1Recovery altimeters separated from transmitting devicesAltimeters have separate compartmentInspection2.13Recovery use commercial low-current e matchesDavyfire N28BR e-matches have been selectedInspection, Testing2121Dual Deployment

22Drogue Parachute5280 feet AGL63 ft/s Main Parachute500 feet AGL13 ft/s

22Avionics BaysCopper mesh shielding

Black Powder WellsAltimetersGPS2323Deployment Altimeters SelectionItemDistributorProductUnit DimensionsUnit CostNumberTotal CostMain AltimeterFeatherweight AltimetersRaven31.8in. X 0.8in. X 0.55in. X 0.34oz$155.002$310.00Backup AltimeterPerfectFliteStratologger2.75in. long X 0.9 in. wide X 0.45 oz$79.952$159.90Option 1Loki ResearchOzark ARTS3.75in. long X 1.4in. wide X 2.75 oz$190.002$380.00Option 2Adept RocketryALTS1-50K0.9in. X 0.65in. X 4.25in. X 4.25oz$89.002$178.0024Full Redunddancy24Deployment Altimeter Wiring

2525Maximum Landing Velocity

2626Calculating Minimum Diameter of Main Parachute

2727Main Parachute SelectionManufacturerItemShroud LinesDiameterUnit CostTop Flight RecoveryTFR Par-1201610ft$89.95The RocketmanSTANDARD LOW-POROSITY 1.1 RIPSTOP PARACHUTE410ft$110.00Fruity ChutesCustom Parachute - 50lb @ 20fps1610ft$240.002828Drift For Main Parachute

2929Maximum Drift For Drogue

3030Minimum Drogue Parachute Diameter

3131Drogue Parachute SelectionManufacturerItemShroud LinesDiameterUnit CostTop FlightPAR-STD-2462ft$9.95The RocketmanSTANDARD LOW-POROSITY 1.1 RIPSTOP42ft$25.00Apogee RocketsNylon Parachute #2921862ft$11.443232Recovery ComponentsProposed SelectionDistributorItem NumberQty.Total CostMain AltimetersFeatherweight AltimetersRaven32$310.00Backup AltimetersPerfectFliteStratoLogger2$159.90Electric MatchesCoast RocketryDaveyfire N28BR4$11.80FFFFg Black PowderGoexGoex 4F Black Powder1$15.75Black Powder Ejection Charge HoldersAerocon SystemsBPSmall1$3.00SwivelsCommonwealth RocketrySWLDK802$3.98Main Shock CordGiant Leap RocketryTubular Kevlar1$37.99Drogue Shock CordGiant Leap RocketryTubular Kevlar1$31.49Main ParachuteTop Flight RecoveryTFR Par-1201$89.95Flameproof Main Parachute Deployment BagRocketman EnterprisesDB81$40.00Drogue ParachuteTop FlightPAR-STD-241$9.95Flame-Proof Drogue Parachute Deployment BagRocketman EnterprisesDB21$25.00U-BoltsSunward AerospaceU-Bolt Assembly - 0.25in. (compact)2$8.58Quick LinksCommonwealth Rocketry0.25in. Stainless Steel Delta Quick Link4$11.96Shear PinsMissile Works2-56 Nylon Shear-Pin (10 pack)1$1.00Arming SwitchesFeatherweight AltimetersFeatherweight Magnetic Switch2$50.00Hand-held Rotary Fan AnemometerWeather ShackSpeedTech WM-3001$154.95GPS SystemBig Red BeeBeeLine GPS-Package Deal2$578.00Radio Frequency Shielding MaterialLessEMFPure Copper Polyester Taffeta Fabric2$21.90Total$1,565.203333Kinetic EnergySectionWeightKinetic EnergyNose Cone2.252 lbs5.662 ftlbfUpperbody Airframe and Payload16.766 lbs42.1533 ftlbfBooster10.602 lbs26.6557 ftlbfTotal29.62 lbs74.471 ftlbf3434Weather Cocking

3535Landing RadiusWind SpeedLanding Radius0 mph7 ft5 mph (7.33 ft/s)275 ft10 mph (14.67 ft/s)550 ft15 mph (22 ft/s)900 ft20 mph (29.33 ft/s)1300 ft360 mph wind speed: Instability directly after launch36Payload3737SMD PayloadAtmospheric Data GatheringAutonomous Real-Time Camera Orientation System (ARTCOS)Video RecordingClear HousingMoving Towards PCB38PCB: Save Space, More Elegant38

39

Payload FrameworkSolar Irradiance andUV SensorsARTCOSCircuit BoardVideo CameraLCD Screen39Atmospheric Data Gathering

4040Precision of Instrumentation41PurposeProductPrecisionBarometric PressureBMP1800.017psiBarometric PressureMS5611-01BA03 0.029psiTemperatureBMP1801.8 FTemperatureMS5611-01BA03 1.44 FHumidityHIH40303.6% RHHumidityHH10D3% RHSolar IrradianceSP-1105%Solar IrradianceTSL25615%Ultraviolent RadiationSU-10010%Ultraviolent RadiationTOCON_ABC310%GPSLS200319.84ftAccelerometerADXL3454.3mgOfficial AltimeterAdept A1E1ft41Autonomous Real-Time Camera Orientation System (ARTCOS)

4242Payload PCB Schematics

4343Scoring Altimeter Adept A1E

NameDistributorDimensionsInput VoltageCostA1EAdept0.55" x 2.2"12V$29.95 StratologgerPerfectFlite2.75" x 0.9"9V$79.95 ARTSLoki Research3.75" x 1.49 - 15V$190.00 4444Payload Verification and Testing SOW#Requirement Satisfying Design FeatureVerification Method3.1Launch vehicle shall carry a science or engineering payloadSMD payload selectionInspection, Analysis3.1.3.1Measurements of pressure, temperature, relative humidity, solar irradiance and ultraviolet radiationAn appropriate sensor for each of these measurements is onboardTesting, Analysis, Inspection3.1.3.2Measurements occur every 5 seconds during descentMain flight computer frequency 16MhzTesting, Analysis3.1.3.3Measurements occur every minute after landingMain flight computer frequency 16MhzTesting, Analysis3.1.3.4Data collection will cease 10 minutes after landingFlight computer halts data collection after 10 minutesTesting, Analysis, Inspection3.1.3.5Take 2 pictures during descent and 3 after landingControl of camera to appropriate image captureTesting3.1.3.6Pictures with sky at top of frame, ground at bottomSelf-leveling camera mountTesting, Inspection3.1.3.7Data stored onboard and transmitted wirelesslymicroSD onboard storage; Xbee Wireless TransimtterTesting3.1.3.8Separations of payload at apogee is allowed, but such separation may cause drifting outside recovery areaThe payload does not detach from the rocket vehicleInspection3.1.3.9Payload will carry GPSLocosys LS20031 is incorporated in the payload designInspection, Testing3.2Data from payload will be collected, analyzed, and reported by team following scientific methodResearch question is the correlation between altitude and atmospheric dataAnalysis3.5Payload must be designed to be recoverable and reusable Mount to rails inside housingTesting, Inspection4545Budget 4646Cost of Vehicle and Payload47SubsystemCostStructure$765Recovery$1383Payload$1558Propulsion$434Total$420247Budget Summary48ElementEst. CostTesting/Prototyping$13,972Outreach$3,669Final Build$4,202Travel to Competition$8,200Total$29,92248Educational Outreach

49Project GoalTo reach 2,500 studentsHighlightProject minimum was reached on the first day of the project >100 studentsMajor eventsStar Party November 9thScience Olympiad February 2349Project Outline50

Reference the project plan section; purpose of this slide is to show that we have testing plans (not enough space to but them here). The deadlines are acknowledged and the team will follow all project plans meticulously, as well as update, correct, and modify them concurrently throughout the course of the entire project50SMD Deliverables Schedule51

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Questions5252