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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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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