ares aloft: martian atmospheric entry and in-situ resource use via cubesat jeffrey stuart jet...
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Ares Aloft: Martian Atmospheric Entry and In-Situ Resource Use via CubeSat
Jeffrey StuartJet Propulsion Laboratory
California Institute of [email protected]
11/20/2014
Copyright 2014 California Institute of Technology. Government sponsorship acknowledged.
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Motivation & Overview
Use Mars 2020 launch opportunity to demonstrate key technologies for future exploration• Mission Concept• Entry, Descent, and Landing (EDL)• In-Situ Resource Use (ISRU)– Enabling technologies
• Feasibility & Benefits
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CubeSat Mission Concept
TMI
Mars 2020
CubeSat
Separation:• Protects Mars 2020• Requires independent operationWhen is best time to separate?
CubeSat EDL:• On same scale as Sojourner• Advancements in state-of-the-art?What methods can be tested by 2020?
ISRU = Propellant Production
How much will we really get?
Pre-Decisional Information -- For Planning and Discussion Purposes Only
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Mars CubeSat EDLSojourner EDL (Heritage)Components• Fixed heat shield• Parachute• Airbags• Solid rockets• Tether & backshell• Landing platform
Image courtesy: Savino & Carandente, 2012
Deployable heat shield• Components
• Heat shield• Parachute
• Low TRL (2-3)• Numerical study
Key Questions• Concept needs to be studied for Mars.
• Will Earth / ISS-based test be beneficial?• How sensitive is concept to entry conditions?• Other advanced EDL concepts to be explored?
Pre-Decisional Information -- For Planning and Discussion Purposes Only
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Mars ISRU
Oxygen (O2)
Water (H2O)
Propellant (CH4)
Support life
Oxygen & Water: ISS electrolysis system Phoenix (water ice) Mars 2020 (MOXIE)
Atmospheric
CO2
Ground
H2O
Support return
Propellant: ISS Sabatier reactor Ground experiments Mars ???
Key Questions• Will ISRU produce sufficient
propellant in time?• Can stored hydrogen be
transported on CubeSat?
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Sabatier reaction
Water electrolysis
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ISRU TechnologySabatier reaction [exothermic]
Water electrolysis
Reverse water-gas-shift (RWGS) process [endothermic]
Images courtesy: Holladay et al., 2007
1/8 scale of reference robotic return mission
Images courtesy: Junaedi et al., 2011
Unit above supports 2 crew
Units shown: TRL 4-6
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Feasibility & Benefits
Mars Entry and Propellant Production Cubesat• Demonstrates:
– CubeSat atmospheric entry, descent, and landing– In-situ propellant production critical for sample or manned return
• Specific architecture proposed:– Mid- to high-TRL for Cubesat-size, full-capability ISRU components– Low TRL deployable heat shield– 6-year development and construction timeline
Pre-Decisional Information -- For Planning and Discussion Purposes Only
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References• Stuart et al. “Mission Report Summary (Team Kanau)”, International
Inspiration Mars Student Design Competition, 1st Place. URL: https://sites.google.com/site/occupyplanet4/final-report-1
• Savino & Carandente, “Aerothermodynamic and Feasibility Study of a Deployable Aerobraking Re-Entry Capsule”, Fluid Dynamics and Materials Processing, vol. 8, no. 4, 2012, pp. 453-476.
• Holladay et al., “Microreactor development for Martian in situ propellant production”, Catalysis Today, vol. 120, 2007, pp. 35-44.
• Brooks et al., “Methanation of carbon dioxide by hydrogen reduction using the Sabatier process in microchannel reactors”, Chemical Engineering Science, vol. 62, 2007, pp. 1161-1170.
• Junaedi et al., “Compact and Lightweight Sabatier Reactor for Carbon Dioxide Reduction”, 41st International Conference on Environmental Systems, Portland, Oregon, 17-21 July 2011, AIAA 2011-5033.
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Helpful Links
JPL CubeSats:http://cubesat.jpl.nasa.gov/
INSPIRE Mission (Earth escape CubeSat):http://cubesat.jpl.nasa.gov/projects/inspire/overview.html
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CubeSat Propulsion
Commercially Available• Aerojet Rocketdyne
– https://www.rocket.com/cubesat
• Busek– http://www.busek.com/cubesatprop__main.htm
In Development• Microfluidic Electrospray Propulsion
– http://microdevices.jpl.nasa.gov/news/news-microfluidic-electrospray-propulsion.php
• CubeSat Ambipolar Thruster– http://pepl.engin.umich.edu/thrusters/CAT.html
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Mars ISRU
Oxygen (O2)
Water (H2O)
Propellant (CH4)
Support life
Oxygen & Water: ISS electrolysis system Phoenix (water ice) Mars 2020 (MOXIE)
Atmospheric
CO2
Ground
H2O
Support return
Propellant: ISS Sabatier reactor Ground experiments Mars ???
Key Questions• Will ISRU produce sufficient
propellant / other material?• Can stored hydrogen be
transported on CubeSat?
Approved for unlimited release