NOON NOON UNOUNO

HIGH-MOBILITY HIGH-MOBILITY MARSMARS

EXPLORATION EXPLORATION SYSTEMSYSTEM

NOON NOON UNOUNO

HIGH-MOBILITY HIGH-MOBILITY MARSMARS

EXPLORATION EXPLORATION SYSTEMSYSTEM

DANIEL MCCAFFERYDANIEL MCCAFFERYJEFF ROBINSONJEFF ROBINSON

KYLE SMITHKYLE SMITHJASON TANGJASON TANG

BRAD THOMPSONBRAD 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

IntroductionIntroductionIntroductionIntroduction

Our MissionOur MissionOur MissionOur 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

functionfunction option 1option 1 option 2option 2 option 3option 3 option 4option 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

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

Rank-Order Rank-Order ObjectivesObjectives

Which objectives are more important?

AA BB CC DD EE 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 ImportanceOrder of Importance

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

Results of VotingResults of Voting Final RankFinal Rankof Importanceof Importance

BradBrad JasonJason DanielDaniel JeffJeff KyleKyle 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%

Establish Scoring SystemEstablish Scoring SystemGood: 3, Average: 0, Worse: -3

Ground TOTapered & SweptCanardRocketAux. Rockets

Ground TOWheels on WingsConv. tailDeltaRocket

SkidsSleeve TORocketDetach. frontCanardTapered

PropellerTaperedConv. tailGround TO

PropellerSweptAux. RocketsV-Tail

RocketDeltaCanardAux. RocketsGround 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

Mars SpacecraftMars Spacecraft

Launch Vehicle Launch Vehicle SelectionSelectionLaunch Vehicle Launch Vehicle SelectionSelection

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

Spacecraft Spacecraft PropulsionPropulsionSpacecraft Spacecraft PropulsionPropulsion

TR-312-100YN Liquid Bi-propellant*

Isp = 330 sec

Thrust = 556 N

Weight = 6.03 kg* Manufactured by TRW

AstrodynamicsAstrodynamicsAstrodynamicsAstrodynamics 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

EntryEntryEntryEntry 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 AircraftMars AircraftMars AircraftMars Aircraft

Aircraft DescriptionAircraft DescriptionAircraft DescriptionAircraft 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

AerodynamicsAerodynamicsAerodynamicsAerodynamics

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

DragCruise – 11.88 NLoiter – 5.82 N

Aircraft PropulsionAircraft PropulsionAircraft PropulsionAircraft Propulsion Aircraft engine - nitrogen

tetroxide (NTO) / monomethyl hydrazine (MMH)

Isp = 290 sec

Max Thrust = 22 N

Mass = 0.7 kg

Carpet PlotCarpet PlotCarpet PlotCarpet PlotConstraints

Sink rate < 10 m/s M < 0.8 Cruise velocity > 160 m/s

Minimize take off mass without violating constraints

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