NASA - USLI Presentation 1/23/2013
University of Minnesota: 2012-2013 USLI CDR 1
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
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Ballasted system ARRD ◦ Staged deployment
Rover ◦ Engineering payload
Removable fin and motor mount Composite airframe Embedded electrical systems ◦ Recovery ◦ Reliability
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Air braking systems removed ◦ Beyond teams current skill level
Light weight, reduced drag ◦ Retractable Rail buttons
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Duel deployment ◦ Drogue and Main
Reduction of avionics improved design ◦ Simplified systems
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Engineering payload Demonstrator ◦ Space exploration technologies
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Flexibility ◦ Key for hitting target altitude
Room for growth ◦ Advanced projects
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Light weight Durable Customizable ◦ Future projects
Modular system ◦ Flexible ◦ Longevity of vehicle and future projects
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Reliable Ease of integration and usage ◦ Critical for quick assembly on flight line
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Flat Cable Screw
E – match
Redundant Wires
75mm L1729 - WT ◦ 3695 N-sec
Reloadable
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𝑉𝑚𝑚𝑚 = 674 𝑓𝑓/𝑠 Mach = 0.69 Peak altitude 𝐴𝐴𝐴 = 5050 𝑓𝑓 ◦ With rail buttons deployed
Retractable rail buttons will increase altitude by 300 – 500 feet ◦ Mission + Vehicle flexibility
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CP: 87.58 inches CG: 76.53 inches Stability margin 1.81
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CG CP
T/W = 10.75 𝑉𝑒𝑚𝑒𝑒 = 70.4529 𝑓𝑓/𝑠
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574 oz (35.875 lb) ◦ With motor ◦ 7% margin of error ◦ Estimations
Room for larger motor is mass flux is significant
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Rocket man Mach 2 36” Kevlar
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Fruity Chutes Iris Ultra 84” Tubular nylon 30 foot harness ◦ 1” X 9/16”
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Nose/Payload Recovery Booster
66.28 ft-lb 54.54 ft-lb 70.68 ft-lb
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Wind Speed (Mph)
Drift Distance (Feet)
5 520
10 1200
15 1700
20 2800*
*Over USLI restriction, but launch is not anticipated under these conditions
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• Open wheel configuration to ensure sufficient ground clearance to traverse rough terrain
• Closed wheel configuration to ensure integration into the rocket
Rover between nose cone and aviation bay
Payload bay 26 inches Sabot caps hold
payload in place
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Sabot system ◦ Sabot support caps ◦ Black powder in piston
in aft sabot cap ◦ Nose cone bulkhead
for forward sabot cap
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RC Camera/RC transmitter
Receiver ArduIMU+V3 Two high torque
servos Battery packs GPS RC On/Off Switch
Ground Station
Rover Control System
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Successful launch Recovery failure
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Avionics bay modification New circuitry scheme Parachute packing issues ◦ Deployment bags
Simplification of overall design
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Date is TBD Test shear pin count ◦ Ground Test
Determine functionality of ARRD and Raven altimeters ◦ Half scale 2
Inspect for damages post test
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University of Minnesota: 2012-2013 USLI CDR 36
System Verification Procedure Verification Status
Heat shielding Measure heat transfer across prototype heat shield
Passed
Rover Structure Determine viability of composite structures
Passed
Recovery systems Staged Deployment
Ground test of recovery system with main and drogue
Feb 15th
Rover Ground testing Navigate and test telemetry features of rover
Feb 15th – March 1st
Payload Deployment Ground test of deployment system with sabot
Feb 15th
Fins and Motor mount Static and comparative prototyping
Feb 15th - 20th
2nd subscale Launch Successfully launch half scale with recovery systems
Feb 18th
Updates Prospective Sponsors
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
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