NASA - USLI Presentation 1/23/2013. University of Minnesota: USLI CDR 1
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1 NASA - USLI Presentation 1/23/ USLI CDR 1
2 Final design Key features Final motor choice Flight profile Stability Mass Drift Parachute Kinetic Energy Staged recovery Payload Integration Interface Status of verification Status of mission 2013 USLI CDR 2
3 2013 USLI CDR 3
4 2013 USLI CDR 4
5 2013 USLI CDR 5
6 Ballasted system ARRD Staged deployment Rover Engineering payload Removable fin and motor mount Composite airframe Embedded electrical systems Recovery Reliability 2013 USLI CDR 6
7 Air braking systems removed Beyond teams current skill level Light weight, reduced drag Retractable Rail buttons 2013 USLI CDR 7
8 Duel deployment Drogue and Main Reduction of avionics improved design Simplified systems 2013 USLI CDR 8
9 Engineering payload Demonstrator Space exploration technologies 2013 USLI CDR 9
10 Flexibility Key for hitting target altitude Room for growth Advanced projects 2013 USLI CDR 10
11 Light weight Durable Customizable Future projects Modular system Flexible Longevity of vehicle and future projects 2013 USLI CDR 11
12 Reliable Ease of integration and usage Critical for quick assembly on flight line E match Flat Cable Screw Redundan t Wires 2013 USLI CDR 12
13 75mm L WT 3695 N-sec Reloadable 2013 USLI CDR 13
14 2013 USLI CDR 14
15 2013 USLI CDR 15
16 V mmm = 674 ff/s Mach = 0.69 Peak altitude AAA = 5050 ff With rail buttons deployed Retractable rail buttons will increase altitude by feet Mission + Vehicle flexibility 2013 USLI CDR 16
17 CP: inches CG: inches Stability margin 1.81 CG CP 2013 USLI CDR 17
18 T/W = V eeee = ff/s 2013 USLI CDR 18
19 574 oz ( lb) With motor 7% margin of error Estimations Room for larger motor is mass flux is significant 2013 USLI CDR 19
20 2013 USLI CDR 20
21 Rocket man Mach 2 36 Kevlar 2013 USLI CDR 21
22 Fruity Chutes Iris Ultra 84 Tubular nylon 30 foot harness 1 X 9/ USLI CDR 22
23 Nose/Payload Recovery Booster ft-lb ft-lb ft-lb 2013 USLI CDR 23
24 Wind Speed (Mph) Drift Distance (Feet) * *Over USLI restriction, but launch is not anticipated under these conditions 2013 USLI CDR 24
25 2013 USLI CDR 25
26 2013 USLI CDR 26
27 Open wheel configuration to ensure sufficient ground clearance to traverse rough terrain Closed wheel configuration to ensure integration into the rocket 2013 USLI CDR 27
28 Rover between nose cone and aviation bay Payload bay 26 inches Sabot caps hold payload in place 2013 USLI CDR 28
29 Sabot system Sabot support caps Black powder in piston in aft sabot cap Nose cone bulkhead for forward sabot cap 2013 USLI CDR 29
30 RC Camera/RC transmitter Receiver ArduIMU+V3 Two high torque servos Battery packs GPS RC On/Off Switch 2013 USLI CDR 30
31 Ground Station Rover Control System 2013 USLI CDR 31
32 2013 USLI CDR 32
33 Successful launch Recovery failure 2013 USLI CDR 33
34 Avionics bay modification New circuitry scheme Parachute packing issues Deployment bags Simplification of overall design 2013 USLI CDR 34
35 Date is TBD Test shear pin count Ground Test Determine functionality of ARRD and Raven altimeters Half scale 2 Inspect for damages post test 2013 USLI CDR 35
36 System Verification Procedure Verification Status Heat shielding Rover Structure Recovery systems Staged Deployment Rover Ground testing Payload Deployment Fins and Motor mount Measure heat transfer across prototype heat shield Determine viability of composite structures Ground test of recovery system with main and drogue Navigate and test telemetry features of rover Ground test of deployment system with sabot Static and comparative prototyping Passed Passed Feb 15 th Feb 15 th March 1 st Feb 15 th Feb 15 th - 20 th 2 nd subscale Launch Successfully launch half scale with recovery systems Feb 18 th 2013 USLI CDR 36
37 Minnesota Space Grant $ 500 UMN Aerospace Department $ 500 UofM Student Union Grant $ 600 Family Fun Fair $ 200 ATK $ 3,000 Exxon Mobile to be negotiated Total Current Funding $ 4,8 00 Updates Prospective Sponsors 2013 USLI CDR 37
38 2013 USLI CDR 38
39 2013 USLI CDR 39
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