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NOON UNO HIGH-MOBILITY MARS EXPLORATION SYSTEM

NOON UNO HIGH-MOBILITY MARS EXPLORATION SYSTEM. DANIEL MCCAFFERY JEFF ROBINSON KYLE SMITH JASON TANG BRAD THOMPSON. Introduction. Studying and exploring Mars is an essential part on the road to putting man on the planet

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NOON UNO HIGH-MOBILITY MARS EXPLORATION SYSTEM

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  1. NOON UNOHIGH-MOBILITY MARSEXPLORATION SYSTEM DANIEL MCCAFFERY JEFF ROBINSON KYLE SMITH JASON TANG BRAD THOMPSON

  2. Introduction • Studying and exploring Mars is an essential part on the road to putting man on the planet • The design makes it an outstanding high-mobility vehicle used for Mars exploration • Very low development, construction, and operation cost

  3. Our Mission • Leave GTO and travel to Mars • Separate from spacecraft and begin flight • Cruise 35 km at 183 m/s (best range) • Loiter at 143 m/s for 45 minutes (best endurance) • Descend at 7.9 m/s (sink rate) in Gusev Crater

  4. Morphological Chart • Breakdown system to feature or component level (lift, propulsion, stability, landing gear, take off)

  5. Rank-Order Objectives • Which objectives are more important? • Order of Importance • 1st – A (weight) • 2nd – D (size) • 3rd – C (stability) • 4th – E (speed) • 5th – B (endurance)

  6. Results of Voting Final Rank of Importance

  7. Establish Scoring System • Good: 3, Average: 0, Worse: -3

  8. Mars Spacecraft

  9. Launch Vehicle Selection • Ariane 4 • $60 million launch cost • 3465 kg boost capability to GTO • 4 meter diameter fairing

  10. Spacecraft Propulsion • TR-312-100YN Liquid Bi-propellant* • Isp = 330 sec • Thrust = 556 N • Weight = 6.03 kg * Manufactured by TRW

  11. Astrodynamics • 185 km altitude about Earth at perigee • 35,786 km altitude about Earth at apogee • At perigee, velocity = 10.25 km/s • 1st burn, velocity increases by 1.159 km/s • v at end of transfer orbit to match Mars’ velocity • 2nd burn, velocity increases by 2.65 km/s • v required to be captured by Mars’ gravity and enter circular orbit at an altitude of 500 km • 3rd burn, velocity decreases by 1.373 km/s • For atmospheric entry: 4th burn, velocity decreases by 0.0958 km/s

  12. Entry • After re-entry into atmosphere, first parachute deploys to reorient spacecraft and takes away heat shield • Main parachute deploys from blunt end of shell and pulls it away • Parachute deploys from the aft end of aircraft and separates it from rest of capsule • Aircraft releases parachute and flies down to cruise altitude

  13. Mars Aircraft

  14. Aircraft Description • Take off mass – 84.5 kg • Wing span – 3.67 m • Fuselage • Length – 3.02 m • Diameter – 0.25 m • Low, swept, tapered wing • Canards • Skids

  15. Aerodynamics NACA 4415 airfoil • Wings - 3 incidence • Main Wings - 20 sweep • Canards – 22.5 sweep • Drag • Cruise – 11.88 N • Loiter – 5.82 N

  16. Aircraft Propulsion • Aircraft engine - nitrogen tetroxide (NTO) / monomethyl hydrazine (MMH) • Isp = 290 sec • Max Thrust = 22 N • Mass = 0.7 kg

  17. Carpet Plot Constraints • Sink rate < 10 m/s • M < 0.8 • Cruise velocity > 160 m/s • Minimize take off mass without violating constraints

  18. ¿Questions?

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