CDR Presentation 1
Presentation Outline # Title # Title 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 Team Introduction Vehicle Overview Vehicle Dimensions Upper Body Section Payload Housing Structure Booster Section Coupler Design Fins Static Margin Diagram Static Stability Margin Final Motor Selection Mass Statement Recovery System Overview Recovery System Components Recovery Electronics Kinetic Energy Summary Landing Radius Testing Overview Test Plans and Procedures Structure Tests Structure Tests Pictures Subscale Flight Results Subscale Flight Results, cont. Subscale Simulated Flight Path 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 Subscale Actual Flight Path Staged Recovery Tests Payload Overview SMD Payload Overview Physical Layout Block Diagram Wireless Transmitter ARTCOS Video Camera Scoring Altimeter Payload PCB Schematics Payload Integration Procedure First Prototype Test Flight Data Test Flight GPS Data Failures and Solutions Interface Status of Requirements Verification Design Verification Public Outreach Progress Educational Outreach What Does NASA Stand For? Questions* 2
Team Introduction 3
Vehicle Overview 4
Vehicle Dimensions Total Length: 109.25 in Upper airframe section: 36.5 in Acrylic payload section: 36 in Booster section: 36.75 in Outer diameter: 5.525 in Upper Body Section Payload Housing Booster Section 5
Upper Body Section Dimensions 36.5 in long.075 in thick (airframe and nosecone) Nose Cone Ballast System Upper Body Airframe 6
Payload Housing Structure Dimensions 36 in long 0.125 in thick Material Clear Acrylic 7
Booster Section Dimensions 36 in long 0.075 in wall thickness Materials Fiberglass 8
Coupler Design Dimensions 11.25 in long Outer diameter 5.373/5.178 in Inner diameter 5.06 in Material Fiberglass 9
Fins Dimension Root Chord 12 in Tip Chord 0 in Height 5 in Sweep Length 9.8 in Sweep Angle 63 Degrees 10
Static Margin Diagram 11
Static Stability Margin Center of Gravity 62.992 in from the tip of the nose Center of Pressure 80.709 in from the tip of the nose Stability margin 17.8 in or 3.22 calibers of body width 12
Final Motor Selection Cesaroni L1720-WT-P Rail Exit Velocity 69.8 ft/s 2.95 in diameter Total impulse of 831 lb f s Estimated apogee at 4,852 ft AGL unballasted 656 ft/s max velocity 2.15 second burn time 13
Mass Statement Subsection Payload 2.47 Recovery 8.20 Structure 26.46 Total Mass (Launch) 37.13 Total Mass (Apogee) 33.25 10.6:1 thrust-to-weight ratio Mass may change by ±10 percent Reduction to weight planned Mass (lb)times acceleration 14
Recovery System Overview 15
Recovery System Components Material 1.9 oz. silicone coated, reinforced cross-form, rip stop nylon Main 10 ft diameter Four 10 ft long 0.625 in wide tubular woven nylon shroud lines 40 ft long 0.25 in wide tubular Kevlar shock cord SkyAngle XXL deployment bag Drogue 2 ft diameter Four 2ft long 0.25 in wide tubular woven nylon shroud lines 20 ft long 0.25 in wide tubular Kevlar shock cord Nomex blanket for protection 16
Recovery Electronics Altimeter System Metallic flashing Shields avionics from false signaling by interfering RF Featherweight magnetic arming switch Primary Featherweight Raven 3 Secondary PerfectFlite Stratologger SL100 Power One 9-volt battery GPS System Transmitter Garmin Astro DC40 Secured to drogue parachute shock cord Handheld Receiver Garmin Astro 320 17
Kinetic Energy Summary Phase Nose Cone and Upper Body Airframe Payload Booster Total Contained Vehicle Apogee to Main (max) Main to Landing (max) 965.6 ft lbf 1280.2 ft lbf 1225.3 ft lbf 3730.3 ft lbf 5.4 ft lbf 17.7 ft lbf 15.9 ft lbf 51.6 ft lbf 18
Landing Radius Wind Speed Landing Radius (ft) 0 mph 7 5 mph (7.33 ft/s) 501 10 mph (14.67 ft/s) 1,156 15 mph (22 ft/s) 1,639 20 mph (29.33 ft/s) 2,243 19
Testing Overview 20
Test Plans and Procedures Subscale Flights Full Scale Flights Pre-Launch Checklists Post-Flight Checklists Timed Assemblies Failure Analysis 21
Structure Tests Component Test Date Description Procedure Success Epoxy Hydraulic Press 12/28/12 Bulkhead epoxied into airframe, then pressed Hydraulic press applied force simulating shock force Yes; epoxy maxed out the scale at 1500 lbs. Fiberglass Bulkhead Strength Hydraulic Press 12/28/12 Bulkhead was placed under incrementing force Hydraulic press pressed on a block of 2 in x 3 in simulating shock force Yes; bulkhead maxed out the scale at 1500 lbs or 250 psi. Airframe testing (both fiberglass and acrylic) Hydraulic Press 1/4/13 Airframes were subjected to force axially Hydraulic press pressed on the center on a steel sheet across the circumference of the acrylic and fiberglass airframes Yes; both withstood 1500 pound shock force, and 1 minute of constant 1500 pound force Fin Test Hydraulic Press 1/5/13 Torque applied to fins until compromised. Fin mount was placed under the hydraulic press and force applied to create torque. Yes, fins withstood a maximum of 550 in-lbf of torque. First eye bolt Test Test Launch 1/7/13 Drogue parachute attached to eye bolt in place of u bolt. Prototype Vehicle was launched using a custom L667. Yes, eye bolt survived the flight. Second eye bolt Test (with weld) Hydraulic Press TBD Force applied to eye bolt via hydraulic press eye bolt is mounted onto a bulkhead and pressed until failure or weight maximum reached TBD 22
Structure Test Pictures 23
Subscale Flight Results Location Date Apogee (AGL) Predicted Apogee (AGL) Video Link Hunewell Ranch 30 November 12 N/A 401 ft N/A Hunewell Ranch 5 December 12 460 ft 450 ft Video Hunewell Ranch 7 December 12 N/A 575 ft N/A Hunewell Ranch 8 December 12 519 ft 600 ft N/A Hunewell Ranch 8 December 12 509 ft 690 ft N/A Hunewell Ranch 14 December 12 N/A 520 ft N/A Asa, TX 15 December 12 666 ft 615 ft N/A Asa, TX 15 December 12 476 ft 530 ft N/A 24
Subscale Flight Results, cont. Location Date Apogee (AGL) Predicted Apogee (AGL) Video Link Hunewell Ranch 19 December 12 929 ft 1848 ft N/A Hunewell Ranch 19 December 12 1,061 ft 1848 ft Video Hunewell Ranch 21 December 12 629 ft 780 ft Video Hunewell Ranch 21 December 12 4,992 ft 5227 ft Video Hunewell Ranch 5 January 13 2,271 ft 3214 ft Video Hunewell Ranch 6 January 13 2,920 ft 3559 ft Video P&L Ranch 7 January 13 2,402 ft 2908 ft N/A 25
Subscale Simulated Flight Path 26
Subscale Actual Flight Path Featherweight Raven3 PerfectFlite Stratologger SL100 27
Staged Recovery Tests Consists of subscale test launches and static ejection tests As noted in the previous table, X successful dual deployments have occurred with subscale flights Upon completion of prototype 2 assembly, recovery systems test will continue These will better simulate final launch conditions for the recovery system 28
Payload Overview 29
SMD Payload Overview Atmospheric Data Gathering Autonomous Real-Time Camera Orientation System (ARTCOS) Video Recording Clear Housing PCB in final design 30
Physical Layout Atmospheric Sensors UV and Solar Irradiance Sensors Video Camera ARTCOS 31
Block Diagram 32
Wireless Transmitter Xbee XSC S3B 33
ARTCOS Concept Mounting 34
Video Camera Keyfob 808 #20 Price: $20 35
Scoring Altimeter Adept A1E Name Distributor Dimensions Input Voltage Cost A1E Adept 0.55" x 2.2" 12V $29.95 36
Payload PCB Schematics Breakout Boards PCB Surface Mount PCB Actual PCB 37
Payload Integration Procedure Payload In Bulkhead Static Bulkhead 38
First Prototype No PCB Slow ARTCOS Image Storage No Magnetic Switch Only 180 o UV 39
Test Flight Data 40
Test Flight GPS Data 41
Failures and Solutions Component Mounting No UV Measurements Temperature Spike ARTCOS Mounting Failure 42
Interfaces Airframe Couplers Rail Buttons Magnetic Switches Electrical Ignition System Telemetry 43
Status of Requirements Verification 44
Design Verification To date the vehicle meets every requirement provided in the SOW The recovery subsystem team will continue verification through test flights Payload has all sensors working together, clear acrylic filtering must be tested 45
Public Outreach Progress 900 800 700 600 500 400 300 200 100 0 46
47
What Does NASA Stand For? National Asteroid and Space Association New Airplanes Super Awesome 48
Questions? 49