NOON UNO HIGH-MOBILITY MARS EXPLORATION SYSTEM DANIEL MCCAFFERY JEFF ROBINSON KYLE SMITH JASON TANG BRAD THOMPSON

 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 IntroductionIntroduction

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

function option 1 option 2 option 3 option 4 lift swept wingunswept wingtapered wingdelta wing propulsion propellerturbopropsolar proprocket stability canardconventional tailvertical wingletsv-tail landing gear skidswheelsparachutedetached front take off rocket assistedsleeve (groundless)explosionmagnetism  Morphological Chart Breakdown system to feature or component level (lift, propulsion, stability, landing gear, take off)

 Rank-Order Objectives Which objectives are more important? ABCDEscore A (weight) ---1½½1 3 B (endurance) C (stability) ½1---½0 2 D (size) ½1½ E (speed)  Order of Importance 1 st – A (weight) 2 nd – D (size) 3 rd – C (stability) 4 th – E (speed) 5 th – B (endurance)

Results of Voting Final Rank of Importance BradJasonDanielJeffKylescore A (weight) B (endurance) C (stability) D (size) E (speed) Weight 40% Endurance 3% Stability 12% Size 27% Speed 18%

 Establish Scoring System Good: 3, Average: 0, Worse: -3 Ground TO Tapered & Swept Canard Rocket Aux. Rockets Ground TO Wheels on Wings Conv. tail Delta Rocket Skids Sleeve TO Rocket Detach. front Canard Tapered Propeller Tapered Conv. tail Ground TO Propeller Swept Aux. Rockets V-Tail Rocket Delta Canard Aux. Rockets Ground TO Weight Endurance Stability Size Speed

Mars Spacecraft

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

Spacecraft Propulsion  TR YN Liquid Bi-propellant* I sp = 330 sec Thrust = 556 N Weight = 6.03 kg * Manufactured by TRW

AstrodynamicsAstrodynamics  185 km altitude about Earth at perigee  35,786 km altitude about Earth at apogee  At perigee, velocity = km/s  1 st burn, velocity increases by km/s   v at end of transfer orbit to match Mars’ velocity  2 nd 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  3 rd burn, velocity decreases by km/s  For atmospheric entry: 4 th burn, velocity decreases by km/s

EntryEntry  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

Mars Aircraft

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

AerodynamicsAerodynamics NACA 4415 airfoil  Wings - 3  incidence  Main Wings - 20  sweep  Canards – 22.5  sweep   Drag Cruise – N Loiter – 5.82 N

Aircraft Propulsion  Aircraft engine - nitrogen tetroxide (NTO) / monomethyl hydrazine (MMH) I sp = 290 sec Max Thrust = 22 N Mass = 0.7 kg

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

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