NOON UNO HIGH-MOBILITY MARS EXPLORATION SYSTEM

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NOON UNOHIGH-MOBILITY MARSEXPLORATION SYSTEM

• DANIEL MCCAFFERY
• JEFF ROBINSON
• KYLE SMITH
• JASON TANG
• BRAD THOMPSON

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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

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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

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

function option 1 option 2 option 3 option 4
lift swept wing unswept wing tapered wing delta wing
propulsion propeller turboprop solar prop rocket
stability canard conventional tail vertical winglets v-tail
landing gear skids wheels parachute detached front
take off rocket assisted sleeve (groundless) explosion magnetism
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• Rank-Order Objectives
• Which objectives are more important?

A B C D E score
A (weight) --- 1 ½ ½ 1 3
B (endurance) 0 --- 0 0 0 0
C (stability) ½ 1 --- ½ 0 2
D (size) ½ 1 ½ --- 1 3
E (speed) 0 1 1 0 --- 2

• Order of Importance
• 1st A (weight)
• 2nd D (size)
• 3rd C (stability)
• 4th E (speed)
• 5th B (endurance)

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Results of Voting
Final Rank of Importance
Brad Jason Daniel Jeff Kyle score
A (weight) 8 8 7 8 9 40
B (endurance) 0 1 0 1 1 3
C (stability) 2 2 4 2 2 12
D (size) 6 5 4 7 5 27
E (speed) 4 4 5 2 3 18
Weight 40
Endurance 3
Stability 12
Size 27
Speed 18
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• 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 3 -3 3 0 0 0
Endurance 3 0 3 0 3 0
Stability 3 0 3 -3 3 3
Size 3 0 3 0 -3 3
Speed 0 0 0 0 0 3
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Mars Spacecraft
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Launch Vehicle Selection

• Ariane 4
• 60 million launch cost
• 3465 kg boost capability to GTO
• 4 meter diameter fairing

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Spacecraft Propulsion

• TR-312-100YN Liquid Bi-propellant
• Isp 330 sec
• Thrust 556 N
• Weight 6.03 kg
• Manufactured by TRW

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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

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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

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Mars Aircraft
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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

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Aerodynamics

• NACA 4415 airfoil
• Wings - 3? incidence
• Main Wings - 20? sweep
• Canards 22.5? sweep

• Drag
• Cruise 11.88 N
• Loiter 5.82 N

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Aircraft Propulsion

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

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Carpet Plot

• Constraints
• Sink rate lt 10 m/s
• M lt 0.8
• Cruise velocity gt 160 m/s
• Minimize take off mass without violating
  constraints

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Questions?