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1 Preliminary Design Review Presentation Tarleton State University NASA USLI 2012-2013

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Presentation Outline #Title 3 4 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 22 23 24 25 26 27 Team Introduction Mission Summary Vehicle Dimensions Vehicle Sections Elliptical Nose Cone Ballast System Upper Body Airframe Payload Housing Structure Booster Section Fins Static Stability Margin Vehicle Safety Verification and Testing Motor Trade and Selection Motor Selection 12:1 Thrust to Weight Ratio Vehicle Verification and Testing Recovery Verification and Testing Dual Deployment Avionics Bays Deployment Altimeters Selection Deployment Altimeters Wiring Maximum Landing Velocity Calculating Minimum Diameter of Main Parachute 28 29 30 31 32 33 34 35 36 37 39 40 41 42 43 44 45 46 48 49 50 51 52 Main Parachute Selection Drift for Main Parachute Maximum Drift for Drogue Minimum Drogue Parachute Diameter Drogue Parachute Selection Deployment Altimeters Wiring Recovery Components Kinetic Energy Weather Cocking Landing Radius SMD Payload Payload Framework Atmospheric Data Gathering Precision of Instrumentation Autonomous Camera Orientation Payload PCB Schematic Scoring Altimeter Selection Payload Verification and Testing Cost of Vehicle and Payload Budget Summary Educational Outreach Project Outline SMD Deliverable Schedule 2

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Team Introduction 3

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Mission Summary Science Mission Directorate Payload Vehicle Recovery 4

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Vehicle Overview 5

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Vehicle Dimensions 108 inches total length 5.525 inch outer diameter 33.5 pounds 6

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Vehicle sections Nose Cone Upper Body Airframe Payload Housing Booster Section 7

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Elliptical Nose Cone Dimensions 13 inch long total 5.5 inch shoulder Material Fiberglass 8

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Ballast System Washers Bulkheads Apogee Altitude Control 9

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Upper Body Airframe Dimensions 28 inches long 0.075 inches thick Material Fiberglass 10

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Payload Housing Structure Dimensions 36 inches long 0.125 inches thick Material Clear Acrylic 11

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Booster Section Dimensions 36 inches long 0.075 inches thick Materials Fiberglass 12

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Fins Dimension Root Chord12 in Tip Chord0 inches Height5 inches Sweep Length 9.8 inches Sweep Angle63 Degrees 13

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Static Stability margin 14 Center of Gravity 65.667 inches from the tip of the nose Center of Pressure 79.738 inches from the tip of the nose Stability margin 14.071 inches or 2.55 calibers of body width

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Vehicle Safety Verification and Testing 15 Structure Testing Lab Prototyping Low Altitude Flights Dual Deployment Testing Force of Impact Testing Full Scale Flights Timed Assemblies

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Motor Trade and Selection Motor Apogee (ft.) Velocity Off Rail (ft./s) Total Impulse Max. Velocity (ft./s) Average Thrust Burn Time (s) Thrust to Weight Ratio Availability/ Cost Cesaroni L1720-WT-P 534576 831 lbfs 3696 Ns 738 394 lbf 1754 N 2.1511.8 High/ $171 Aerotech L1390G 561866 887 lbfs 3949 Ns 723 309 lbf 1374 N 2.659.2 Medium/ $210 Cesaroni L1090SS-P 647977 1082 lbfs 4815 Ns 733 247 lbf 1097 N 4.47.4 Medium/ $347 16

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Motor Selection Cesaroni L1720-WT-P Rail Exit Velocity 76 ft/s 2.95 inch diameter Total impulse of 831 lb f -s Estimated apogee at 5345 ft unballasted 738 ft/s max velocity 2.15 second burn time 17

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12:1 Thrust to Weight Ratio 18

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Vehicle Verification and Testing SOW#Vehicle RequirementSatisfying Design FeatureVerification Method 1.1Deliver payload to 5,280 feet AGLMotor selectionTesting, Simulation 1.2Carry official scoring barometric altimeterAdept A1E is included in the payload housingInspection 1.3Launch vehicle remains subsonicMotor selectionTesting, Analysis 1.4Vehicle must be recoverable and reusableRecovery system allows a safe landing of vehicleTesting, Inspection, Analysis 1.5Vehicle has a maximum of four sectionsVehicle is composed of 3 tethered sectionsInspection 1.6Vehicle prepared for flight within 2 hoursLaunch operations and assembly procedureTesting, Inspection 1.7Launch-ready for a minimum of one hourCritical on-board components run for 1.5 hoursTesting, Inspection, Analysis 1.8Vehicle compatible with 8 feet long 1 inch rail1010 rail buttons attached to vehicle bodyInspection 1.9Launch vehicle use 12 volt DC firing systemMotor is compatible with firing systemInspection 1.11Commercially available, certified APCP motorMotor Selection: Cesaroni L1720Inspection 1.12Total impulse under 5,120 Ns3695.6 NsInspection 1.15 Final vehicle successfully launched and recovered prior to FRR Testing ScheduleTesting 19

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Recovery 20

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Recovery Verification and Testing SOW# Recovery System Requirement Satisfying Design FeatureVerification Method 2.1Dual Deployment RecoveryAltimeters fire at the prescribed altitudesTesting 2.2Maximum KE of 75 ft-lbf.Main parachute selectionTesting, Analysis 2.32500ft Landing RadiusDrogue and main parachute selectionTesting, Analysis 2.4Independent Recovery ElectronicsAltimeters have dedicated Power SuppliesInspection 2.5Redundant AltimetersDeployment by main and backup altimeterInspection 2.6External Arming SwitchesPort holes in vehicle airframe to altimeter baysInspection 2.7Each altimeter have a dedicated power supplyEach altimeter uses a separate 9 Volt batteryInspection 2.8Arming switches able to be locked ONPort holes in vehicle airframe to altimeter baysTesting, Inspection 2.9Arming switches located max of 6ft from baseMain altimeter bay is located at 5 8Inspection 2. 10Use removable shear pinsNylon shear pins couple parachute compartmentsInspection 2.11Vehicle carry an electronic tracking device GPS in payload and altimeter baysTesting 2.12 Recovery electronics not disrupted by other electronics Altimeters shielded by copper mesh liningInspection, Testing 2.12.1 Recovery altimeters separated from transmitting devices Altimeters have separate compartmentInspection 2.13Recovery use commercial low-current e matchesDavyfire N28BR e-matches have been selectedInspection, Testing 21

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Dual Deployment 22 Drogue Parachute 5280 feet AGL 63 ft/s Main Parachute 500 feet AGL 13 ft/s

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Avionics Bays Copper mesh shielding Black Powder Wells Altimeters GPS 23

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Deployment Altimeters Selection ItemDistributorProduct Unit Dimensions Unit Cost Number Total Cost Main Altimeter Featherweight Altimeters Raven3 1.8in. X 0.8in. X 0.55in. X 0.34oz $155.002$310.00 Backup Altimeter PerfectFliteStratologger 2.75in. long X 0.9 in. wide X 0.45 oz $79.952$159.90 Option 1Loki ResearchOzark ARTS 3.75in. long X 1.4in. wide X 2.75 oz $190.002$380.00 Option 2 Adept Rocketry ALTS1-50K 0.9in. X 0.65in. X 4.25in. X 4.25oz $89.002$178.00 24

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Deployment Altimeter Wiring 25

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Maximum Landing Velocity 26

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Calculating Minimum Diameter of Main Parachute 27

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Main Parachute Selection ManufacturerItem Shroud Lines Diameter Unit Cost Top Flight Recovery TFR Par-1201610ft$89.95 The Rocketman STANDARD LOW-POROSITY 1.1 RIPSTOP PARACHUTE 410ft$110.00 Fruity ChutesCustom Parachute - 50lb @ 20fps1610ft$240.00 28

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Drift For Main Parachute 29

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Maximum Drift For Drogue 30

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Minimum Drogue Parachute Diameter 31

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Drogue Parachute Selection ManufacturerItem Shroud Lines Diameter Unit Cost Top FlightPAR-STD-2462ft$9.95 The Rocketman STANDARD LOW- POROSITY 1.1 RIPSTOP 42ft$25.00 Apogee Rockets Nylon Parachute #2921862ft$11.44 32

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Recovery Components Proposed SelectionDistributorItem NumberQty.Total Cost Main AltimetersFeatherweight AltimetersRaven32$310.00 Backup AltimetersPerfectFliteStratoLogger2$159.90 Electric MatchesCoast RocketryDaveyfire N28BR4$11.80 FFFFg Black PowderGoexGoex 4F Black Powder1$15.75 Black Powder Ejection Charge HoldersAerocon SystemsBPSmall1$3.00 SwivelsCommonwealth RocketrySWLDK802$3.98 Main Shock CordGiant Leap RocketryTubular Kevlar1$37.99 Drogue Shock CordGiant Leap RocketryTubular Kevlar1$31.49 Main ParachuteTop Flight RecoveryTFR Par-1201$89.95 Flameproof Main Parachute Deployment BagRocketman EnterprisesDB81$40.00 Drogue ParachuteTop FlightPAR-STD-241$9.95 Flame-Proof Drogue Parachute Deployment Bag Rocketman EnterprisesDB21$25.00 U-BoltsSunward AerospaceU-Bolt Assembly - 0.25in. (compact)2$8.58 Quick LinksCommonwealth Rocketry0.25in. Stainless Steel Delta Quick Link4$11.96 Shear PinsMissile Works2-56 Nylon Shear-Pin (10 pack)1$1.00 Arming SwitchesFeatherweight AltimetersFeatherweight Magnetic Switch2$50.00 Hand-held Rotary Fan AnemometerWeather ShackSpeedTech WM-3001$154.95 GPS SystemBig Red BeeBeeLine GPS-Package Deal2$578.00 Radio Frequency Shielding MaterialLessEMFPure Copper Polyester Taffeta Fabric2$21.90 Total$1,565.20 33

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Kinetic Energy SectionWeightKinetic Energy Nose Cone2.252 lbs5.662 ftlbf Upperbody Airframe and Payload 16.766 lbs42.1533 ftlbf Booster10.602 lbs26.6557 ftlbf Total29.62 lbs74.471 ftlbf 34

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Weather Cocking 35

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Landing Radius Wind SpeedLanding Radius 0 mph7 ft 5 mph (7.33 ft/s)275 ft 10 mph (14.67 ft/s)550 ft 15 mph (22 ft/s)900 ft 20 mph (29.33 ft/s)1300 ft 36

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Payload 37

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SMD Payload Atmospheric Data Gathering Autonomous Real-Time Camera Orientation System (ARTCOS) Video Recording Clear Housing Moving Towards PCB 38

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39 Payload Framework Solar Irradiance and UV Sensors ARTCOS Circuit Board Video Camera LCD Screen

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Atmospheric Data Gathering 40

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Precision of Instrumentation 41 PurposeProductPrecision Barometric PressureBMP1800.017psi Barometric PressureMS5611-01BA030.029psi TemperatureBMP1801.8 F TemperatureMS5611-01BA031.44 F HumidityHIH40303.6% RH HumidityHH10D3% RH Solar IrradianceSP-1105% Solar IrradianceTSL25615% Ultraviolent RadiationSU-10010% Ultraviolent RadiationTOCON_ABC310% GPSLS200319.84ft AccelerometerADXL3454.3mg Official AltimeterAdept A1E1ft

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Autonomous Real-Time Camera Orientation System (ARTCOS) 42

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Payload PCB Schematics 43

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Educational Outreach 49 Project Goal To reach 2,500 students Highlight Project minimum was reached on the first day of the project >100 students Major events Star Party November 9th Science Olympiad February 23

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Project Outline 50

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SMD Deliverables Schedule 51

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Questions 52