1 Preliminary Design Review Presentation Tarleton State University NASA USLI

Presentation Outline #Title 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 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

Team Introduction 3

Mission Summary Science Mission Directorate Payload Vehicle Recovery 4

Vehicle Overview 5

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

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

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

Ballast System Washers Bulkheads Apogee Altitude Control 9

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

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

Booster Section Dimensions 36 inches long inches thick Materials Fiberglass 12

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

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

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

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 lbfs 3696 Ns lbf 1754 N High/ $171 Aerotech L1390G lbfs 3949 Ns lbf 1374 N Medium/ $210 Cesaroni L1090SS-P lbfs 4815 Ns lbf 1097 N Medium/ $347 16

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

12:1 Thrust to Weight Ratio 18

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 Ns NsInspection 1.15 Final vehicle successfully launched and recovered prior to FRR Testing ScheduleTesting 19

Recovery 20

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 ft 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’ 8”Inspection 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 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

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

Avionics Bays Copper mesh shielding Black Powder Wells Altimeters GPS 23

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 $ $ Backup Altimeter PerfectFliteStratologger 2.75in. long X 0.9 in. wide X 0.45 oz $79.952$ Option 1Loki ResearchOzark ARTS 3.75in. long X 1.4in. wide X 2.75 oz $ $ Option 2 Adept Rocketry ALTS1-50K 0.9in. X 0.65in. X 4.25in. X 4.25oz $89.002$

Deployment Altimeter Wiring 25

Maximum Landing Velocity 26

Calculating Minimum Diameter of Main Parachute 27

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

Drift For Main Parachute 29

Maximum Drift For Drogue 30

Minimum Drogue Parachute Diameter 31

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

Recovery Components Proposed SelectionDistributorItem NumberQty.Total Cost Main AltimetersFeatherweight AltimetersRaven32$ Backup AltimetersPerfectFliteStratoLogger2$ 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 in. (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$50.00 Hand-held Rotary Fan AnemometerWeather ShackSpeedTech WM-3001$ GPS SystemBig Red BeeBeeLine GPS-Package Deal2$ Radio Frequency Shielding MaterialLessEMFPure Copper Polyester Taffeta Fabric2$21.90 Total$1,

Kinetic Energy SectionWeightKinetic Energy Nose Cone2.252 lbs5.662 ft∙lbf Upperbody Airframe and Payload lbs ft∙lbf Booster lbs ft∙lbf Total29.62 lbs ft∙lbf 34

Weather Cocking 35

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

Payload 37

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

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

Atmospheric Data Gathering 40

Precision of Instrumentation 41 PurposeProductPrecision Barometric PressureBMP180±0.017psi Barometric PressureMS BA03±0.029psi TemperatureBMP180±1.8° F TemperatureMS BA03±1.44° F HumidityHIH4030±3.6% RH HumidityHH10D±3% RH Solar IrradianceSP-110±5% Solar IrradianceTSL2561±5% Ultraviolent RadiationSU-100±10% Ultraviolent RadiationTOCON_ABC3±10% GPSLS20031±9.84ft AccelerometerADXL345±4.3mg Official AltimeterAdept A1E±1ft

Autonomous Real-Time Camera Orientation System (ARTCOS) 42

Payload PCB Schematics 43

Scoring Altimeter Adept A1E NameDistributorDimensionsInput VoltageCost A1EAdept0.55" x 2.2"12V$29.95 StratologgerPerfectFlite2.75" x 0.9"9V$79.95 ARTSLoki Research3.75" x 1.4”9 - 15V$

Payload Verification and Testing SOW#RequirementSatisfying Design FeatureVerification Method 3.1Launch vehicle shall carry a science or engineering payloadSMD payload selectionInspection, Analysis Measurements of pressure, temperature, relative humidity, solar irradiance and ultraviolet radiation An appropriate sensor for each of these measurements is onboard Testing, Analysis, Inspection Measurements occur every 5 seconds during descentMain flight computer frequency 16MhzTesting, Analysis Measurements occur every minute after landingMain flight computer frequency 16MhzTesting, Analysis Data collection will cease 10 minutes after landing Flight computer halts data collection after 10 minutes Testing, Analysis, Inspection Take 2 pictures during descent and 3 after landing Control of camera to appropriate image capture Testing Pictures with sky at top of frame, ground at bottomSelf-leveling camera mountTesting, Inspection Data stored onboard and transmitted wirelessly microSD onboard storage; Xbee Wireless Transimtter Testing Separations of payload at apogee is allowed, but such separation may cause drifting outside recovery area The payload does not detach from the rocket vehicle Inspection Payload will carry GPS Locosys LS20031 is incorporated in the payload design Inspection, Testing 3.2 Data from payload will be collected, analyzed, and reported by team following scientific method Research question is the correlation between altitude and atmospheric data Analysis 3.5Payload must be designed to be recoverable and reusableMount to rails inside housingTesting, Inspection 45

Budget 46

Cost of Vehicle and Payload 47 SubsystemCost Structure$765 Recovery$1383 Payload$1558 Propulsion$434 Total$4202

Budget Summary 48 ElementEst. Cost Testing/Prototyping$13,972 Outreach$3,669 Final Build$4,202 Travel to Competition$8,200 Total$29,922

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

Project Outline 50

SMD Deliverables Schedule 51

Questions 52