Preliminary Design Review Presentation Tarleton State University NASA USLI

Transcription

1 Preliminary Design Review Presentation Tarleton State University NASA USLI

2 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

3 Team Introduction 3

4 Mission Summary Science Mission Directorate Payload Vehicle Recovery 4

5 Vehicle Overview 5

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

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

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

9 Ballast System Washers Bulkheads Apogee Altitude Control 9

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

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

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

13 Fins Dimension Root Chord 12 in Tip Chord 0 inches Height 5 inches Sweep Length 9.8 inches Sweep Angle 63 Degrees 13

14 Static Stability margin 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 14

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

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

17 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

18 12:1 Thrust to Weight Ratio 18

19 Vehicle Verification and Testing SOW# Vehicle Requirement Satisfying Design Feature Verification Method 1.1 Deliver payload to 5,280 feet AGL Motor selection Testing, Simulation 1.2 Carry official scoring barometric altimeter Adept A1E is included in the payload housing Inspection 1.3 Launch vehicle remains subsonic Motor selection Testing, Analysis 1.4 Vehicle must be recoverable and reusable Recovery system allows a safe landing of vehicle Testing, Inspection, Analysis 1.5 Vehicle has a maximum of four sections Vehicle is composed of 3 tethered sections Inspection 1.6 Vehicle prepared for flight within 2 hours Launch operations and assembly procedure Testing, Inspection 1.7 Launch-ready for a minimum of one hour Critical on-board components run for 1.5 hours Testing, Inspection, Analysis 1.8 Vehicle compatible with 8 feet long 1 inch rail 1010 rail buttons attached to vehicle body Inspection 1.9 Launch vehicle use 12 volt DC firing system Motor is compatible with firing system Inspection 1.11 Commercially available, certified APCP motor Motor Selection: Cesaroni L1720 Inspection 1.12 Total impulse under 5,120 Ns Ns Inspection 1.15 Final vehicle successfully launched and recovered prior to FRR Testing Schedule Testing 19

20 Recovery 20

21 Recovery Verification and Testing SOW# Recovery System Requirement Satisfying Design Feature Verification Method 2.1 Dual Deployment Recovery Altimeters fire at the prescribed altitudes Testing 2.2 Maximum KE of 75 ft-lbf. Main parachute selection Testing, Analysis ft Landing Radius Drogue and main parachute selection Testing, Analysis 2.4 Independent Recovery Electronics Altimeters have dedicated Power Supplies Inspection 2.5 Redundant Altimeters Deployment by main and backup altimeter Inspection 2.6 External Arming Switches Port holes in vehicle airframe to altimeter bays Inspection 2.7 Each altimeter have a dedicated power supply Each altimeter uses a separate 9 Volt battery Inspection 2.8 Arming switches able to be locked ON Port holes in vehicle airframe to altimeter bays Testing, Inspection 2.9 Arming switches located max of 6ft from base Main altimeter bay is located at 5 8 Inspection Use removable shear pins Nylon shear pins couple parachute compartments Inspection 2.11 Vehicle carry an electronic tracking device GPS in payload and altimeter bays Testing Recovery electronics not disrupted by other electronics Recovery altimeters separated from transmitting devices Altimeters shielded by copper mesh lining Altimeters have separate compartment Inspection, Testing Inspection 2.13 Recovery use commercial low-current e matches Davyfire N28BR e-matches have been selected Inspection, Testing 21

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

23 Avionics Bays Copper mesh shielding Black Powder Wells Altimeters GPS 23

24 Deployment Altimeters Selection Item Distributor Product Main Altimeter Backup Altimeter Featherweight Altimeters PerfectFlite Raven3 Stratologger Option 1 Loki Research Ozark ARTS Option 2 Adept Rocketry ALTS1-50K Unit Dimensions 1.8in. X 0.8in. X 0.55in. X 0.34oz 2.75in. long X 0.9 in. wide X 0.45 oz 3.75in. long X 1.4in. wide X 2.75 oz 0.9in. X 0.65in. X 4.25in. X 4.25oz Unit Cost Number Total Cost $ $ $ $ $ $ $ $

25 Deployment Altimeter Wiring 25

26 Maximum Landing Velocity 26

27 Calculating Minimum Diameter of Main Parachute 27

28 Main Parachute Selection Manufacturer Top Flight Recovery The Rocketman Item Shroud Lines Diameter Unit Cost TFR Par ft $89.95 STANDARD LOW-POROSITY 1.1 RIPSTOP PARACHUTE 4 10ft $ Fruity Chutes Custom Parachute - 20fps 16 10ft $

29 Drift For Main Parachute 29

30 Maximum Drift For Drogue 30

31 Minimum Drogue Parachute Diameter 31

32 Drogue Parachute Selection Manufacturer Item Shroud Lines Diameter Unit Cost Top Flight PAR-STD ft $9.95 The Rocketman Apogee Rockets STANDARD LOW- POROSITY 1.1 RIPSTOP 4 2ft $25.00 Nylon Parachute # ft $

33 Recovery Components Proposed Selection Distributor Item Number Qty. Total Cost Main Altimeters Featherweight Altimeters Raven3 2 $ Backup Altimeters PerfectFlite StratoLogger 2 $ Electric Matches Coast Rocketry Daveyfire N28BR 4 $11.80 FFFFg Black Powder Goex Goex 4F Black Powder 1 $15.75 Black Powder Ejection Charge Holders Aerocon Systems BPSmall 1 $3.00 Swivels Commonwealth Rocketry SWLDK80 2 $3.98 Main Shock Cord Giant Leap Rocketry Tubular Kevlar 1 $37.99 Drogue Shock Cord Giant Leap Rocketry Tubular Kevlar 1 $31.49 Main Parachute Top Flight Recovery TFR Par $89.95 Flameproof Main Parachute Deployment Bag Rocketman Enterprises DB8 1 $40.00 Drogue Parachute Top Flight PAR-STD-24 1 $9.95 Flame-Proof Drogue Parachute Deployment Bag Rocketman Enterprises DB2 1 $25.00 U-Bolts Sunward Aerospace U-Bolt Assembly in. (compact) 2 $8.58 Quick Links Commonwealth Rocketry 0.25in. Stainless Steel Delta Quick Link 4 $11.96 Shear Pins Missile Works 2-56 Nylon Shear-Pin (10 pack) 1 $1.00 Arming Switches Featherweight Altimeters Featherweight Magnetic Switch 2 $50.00 Hand-held Rotary Fan Anemometer Weather Shack SpeedTech WM $ GPS System Big Red Bee BeeLine GPS-Package Deal 2 $ Radio Frequency Shielding Material LessEMF Pure Copper Polyester Taffeta Fabric 2 $21.90 Total $1,

34 Kinetic Energy Section Weight Kinetic Energy Nose Cone lbs ft lbf Upperbody Airframe and Payload lbs ft lbf Booster lbs ft lbf Total lbs ft lbf 34

35 Weather Cocking 35

36 Landing Radius Wind Speed Landing Radius 0 mph 7 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

37 Payload 37

38 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 39

40 Atmospheric Data Gathering 40

41 Precision of Instrumentation Purpose Product Precision Barometric Pressure BMP180 ±0.017psi Barometric Pressure MS BA03 ±0.029psi Temperature BMP180 ±1.8 F Temperature MS BA03 ±1.44 F Humidity HIH4030 ±3.6% RH Humidity HH10D ±3% RH Solar Irradiance SP-110 ±5% Solar Irradiance TSL2561 ±5% Ultraviolent Radiation SU-100 ±10% Ultraviolent Radiation TOCON_ABC3 ±10% GPS LS20031 ±9.84ft Accelerometer ADXL345 ±4.3mg Official Altimeter Adept A1E ±1ft 41

42 Autonomous Real-Time Camera Orientation System (ARTCOS) 42

43 Payload PCB Schematics 43

44 Scoring Altimeter Adept A1E Name Distributor Dimensions Input Voltage Cost A1E Adept 0.55" x 2.2" 12V $29.95 Stratologger PerfectFlite 2.75" x 0.9" 9V $79.95 ARTS Loki Research 3.75" x V $

45 Payload Verification and Testing SOW# Requirement Satisfying Design Feature Verification Method 3.1 Launch vehicle shall carry a science or engineering payload SMD payload selection Inspection, 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 descent Main flight computer frequency 16Mhz Testing, Analysis Measurements occur every minute after landing Main flight computer frequency 16Mhz Testing, Analysis Data collection will cease 10 minutes after landing Take 2 pictures during descent and 3 after landing Flight computer halts data collection after 10 minutes Control of camera to appropriate image capture Testing, Analysis, Inspection Testing Pictures with sky at top of frame, ground at bottom Self-leveling camera mount Testing, Inspection Data stored onboard and transmitted wirelessly Separations of payload at apogee is allowed, but such separation may cause drifting outside recovery area Payload will carry GPS 3.2 Data from payload will be collected, analyzed, and reported by team following scientific method microsd onboard storage; Xbee Wireless Transimtter The payload does not detach from the rocket vehicle Locosys LS20031 is incorporated in the payload design Research question is the correlation between altitude and atmospheric data Testing Inspection Inspection, Testing Analysis 3.5 Payload must be designed to be recoverable and reusable Mount to rails inside housing Testing, Inspection 45

46 Budget 46

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

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

49 Educational Outreach 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 49

50 Project Outline 50

51 SMD Deliverables Schedule 51

52 Questions 52