Mars Atmospheric Vehicle Feasibility Study

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Mars Atmospheric Vehicle Feasibility Study

• STEC 2005 Presentation
• MSc Astronautics Space Engineering
• Group Design Project

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Agenda

• Background
• Science Payload
• Alternative Configurations
• Balloon Design
• Mission Profile

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Introduction

• Cranfield University MSc in Astronautics and
  Space Engineering
• Lectures
• Group Design Project
• Research Thesis
• 2004/2005 Mars Atmospheric Vehicle
• Nine member team

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Background

• Mars orbiters, landers and rovers.
• No atmospheric vehicles yet.
• Atmospheric vehicles provide many advantages
• Perform ground surveys at close range.
• Cover large areas of Mars.
• Sample atmosphere.
• Deploy small payloads.
• Mars atmosphere difficult to fly in.

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Science Goals

• Determine if life ever arose on Mars.
• Gain understanding of Martian environment.
• Characterise the geology of Mars.
• Characterise the climate of Mars.
• Regions
• Polar caps
• Canyons e.g. Valles Marineris

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Science Payload

• Ten instruments, chosen to perform useful science.

Mass Spectrometer
Ground Penetrating Radar
Video Camera
Pancam
MET Package Wind Sensor
Mini Thermal Emission Spectrometer
Mag Sensor
MET Package Pressure Sensor
MET Package Temperature Sensor
UV Sensor
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Vehicle Configurations

• Baseline aircraft.
• May not be optimal
• Very short duration.
• No chance of landing.
• Researched alternative vehicles and past
  proposals.
• Created matrix of vehicle concepts.

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Trade-off Analysis

• Weighted trade-off parameters such as
• Flight endurance
• Scientific output
• Landing capability
• Controllability
• Performed trade-off analysis.
• Highest scoring options Blimp Balloon.
• Blimp not feasible.
• BALLOON chosen as final configuration.

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System Level Options

• Placing transfer vehicle in orbit vs. flyby
• Balloon communications.
• Flexible time for aeroshell release.
• Polar orbit
• All survey sites are possible.

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Balloon Design

• Pumpkin shaped balloon chosen.
• Sizing 32 metre diameter required to carry 20 kg
  payload.
• Mylar polyester film shell.
• Consists of gores and high strength Kevlar
  tendons.

21.44 m
32 m
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Balloon Design
Stress Analysis of Balloon Gore
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Gondola Design
Gondola Power Equipment

• Protects instrumentation from Martian atmosphere.
• Hangs 5 metres below the balloon.
• Gondola dimensions 360370480 mm.

Mass Spec
Video Camera
Mini TES
Comms Equipment
Pan Cams
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Launch, Transfer Arrival

• Launched on a Delta II 7925 from Cape Canaveral.
• Hohman transfer to Mars.

• Attaining Mars orbit
• Aerobraking used to reduce required propellant.
• ?V required 1.927 km/s
• Polar, sunsynchronous orbit at 600 km altitude.

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Descent Deployment

• Release mechanism
• Low shock required.
• Shape memory alloy.
• Auxiliary device fired on release to inject into
  entry trajectory ellipse.
• Deployment
• Initial parachute deployed.
• Heatshield released.
• Main parachute deployed and inflation started.
• Slow inflation initially, then fast until
  completion.
• Inflation system dropped from balloon.

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Mission Profile

• Mission can last up to 90 days.
• Balloon flies at 5 km altitude.
• Performs science, and drops secondary payloads.

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THORBalloon Mission to MarsTopographical
High-res Observational Researcher
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Mission Cost
Total Cost Euro 86 M
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Acknowledgements
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Questions