Presentation Outline. # Title # Title

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1 CDR Presentation 1

2 Presentation Outline # Title # Title 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 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

3 Team Introduction 3

4 Vehicle Overview 4

5 Vehicle Dimensions Total Length: in Upper airframe section: 36.5 in Acrylic payload section: 36 in Booster section: in Outer diameter: in Upper Body Section Payload Housing Booster Section 5

6 Upper Body Section Dimensions 36.5 in long.075 in thick (airframe and nosecone) Nose Cone Ballast System Upper Body Airframe 6

7 Payload Housing Structure Dimensions 36 in long in thick Material Clear Acrylic 7

8 Booster Section Dimensions 36 in long in wall thickness Materials Fiberglass 8

9 Coupler Design Dimensions in long Outer diameter 5.373/5.178 in Inner diameter 5.06 in Material Fiberglass 9

10 Fins Dimension Root Chord 12 in Tip Chord 0 in Height 5 in Sweep Length 9.8 in Sweep Angle 63 Degrees 10

11 Static Margin Diagram 11

12 Static Stability Margin Center of Gravity in from the tip of the nose Center of Pressure in from the tip of the nose Stability margin 17.8 in or 3.22 calibers of body width 12

13 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

14 Mass Statement Subsection Payload 2.47 Recovery 8.20 Structure Total Mass (Launch) Total Mass (Apogee) :1 thrust-to-weight ratio Mass may change by ±10 percent Reduction to weight planned Mass (lb)times acceleration 14

15 Recovery System Overview 15

16 Recovery System Components Material 1.9 oz. silicone coated, reinforced cross-form, rip stop nylon Main 10 ft diameter Four 10 ft long 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

17 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

18 Kinetic Energy Summary Phase Nose Cone and Upper Body Airframe Payload Booster Total Contained Vehicle Apogee to Main (max) Main to Landing (max) ft lbf ft lbf ft lbf ft lbf 5.4 ft lbf 17.7 ft lbf 15.9 ft lbf 51.6 ft lbf 18

19 Landing Radius Wind Speed Landing Radius (ft) 0 mph 7 5 mph (7.33 ft/s) mph (14.67 ft/s) 1, mph (22 ft/s) 1, mph (29.33 ft/s) 2,243 19

20 Testing Overview 20

21 Test Plans and Procedures Subscale Flights Full Scale Flights Pre-Launch Checklists Post-Flight Checklists Timed Assemblies Failure Analysis 21

22 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

23 Structure Test Pictures 23

24 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 ft 450 ft Video Hunewell Ranch 7 December 12 N/A 575 ft N/A Hunewell Ranch 8 December ft 600 ft N/A Hunewell Ranch 8 December ft 690 ft N/A Hunewell Ranch 14 December 12 N/A 520 ft N/A Asa, TX 15 December ft 615 ft N/A Asa, TX 15 December ft 530 ft N/A 24

25 Subscale Flight Results, cont. Location Date Apogee (AGL) Predicted Apogee (AGL) Video Link Hunewell Ranch 19 December ft 1848 ft N/A Hunewell Ranch 19 December 12 1,061 ft 1848 ft Video Hunewell Ranch 21 December 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

26 Subscale Simulated Flight Path 26

27 Subscale Actual Flight Path Featherweight Raven3 PerfectFlite Stratologger SL100 27

28 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

29 Payload Overview 29

30 SMD Payload Overview Atmospheric Data Gathering Autonomous Real-Time Camera Orientation System (ARTCOS) Video Recording Clear Housing PCB in final design 30

31 Physical Layout Atmospheric Sensors UV and Solar Irradiance Sensors Video Camera ARTCOS 31

32 Block Diagram 32

33 Wireless Transmitter Xbee XSC S3B 33

34 ARTCOS Concept Mounting 34

35 Video Camera Keyfob 808 #20 Price: $20 35

36 Scoring Altimeter Adept A1E Name Distributor Dimensions Input Voltage Cost A1E Adept 0.55" x 2.2" 12V $

37 Payload PCB Schematics Breakout Boards PCB Surface Mount PCB Actual PCB 37

38 Payload Integration Procedure Payload In Bulkhead Static Bulkhead 38

39 First Prototype No PCB Slow ARTCOS Image Storage No Magnetic Switch Only 180 o UV 39

40 Test Flight Data 40

41 Test Flight GPS Data 41

42 Failures and Solutions Component Mounting No UV Measurements Temperature Spike ARTCOS Mounting Failure 42

43 Interfaces Airframe Couplers Rail Buttons Magnetic Switches Electrical Ignition System Telemetry 43

44 Status of Requirements Verification 44

45 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

46 Public Outreach Progress

47 47

48 What Does NASA Stand For? National Asteroid and Space Association New Airplanes Super Awesome 48

49 Questions? 49