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Development of a Two-Stage Mars Ascent Vehicle Using In-Situ Propellant ProductionMars Sample Return (MSR) and Mars In-Situ Resource Utilization (ISRU) present two main challenges for the advancement of Mars science. MSR would demonstrate Mars lift-off capability, while ISRU would test the ability to produce fuel and oxidizer using Martian resources, a crucial step for future human missions. A two-stage Mars Ascent Vehicle (MAV) concept was developed to support sample return as well as in-situ propellant production. The MAV would be powered by a solid rocket first stage and a LOX-propane second stage. A liquid second-stage provides higher orbit insertion reliability than a solid second stage as well as a degree of complexity eventually required for manned missions. Propane in particular offers comparable performance to methane without requiring cryogenic storage. The total MAV mass would be 119.9 kg to carry an 11 kg payload to orbit. The feasibility of in-situ fuel and oxidizer production was also examined. Two potential schemes were evaluated for production capability, size and power requirements. The schemes examined utilize CO2 and water as starting blocks to produce LOX and a propane blend. The infrastructure required to fuel and launch the MAV was also explored.
Document ID
20160008195
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Paxton, Laurel
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Vaughan, David
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
July 1, 2016
Publication Date
May 5, 2014
Subject Category
Spacecraft Design, Testing And Performance
Propellants And Fuels
Meeting Information
Meeting: International Conference on Space Operations (SpceOps 2014)
Location: Pasadena, CA
Country: United States
Start Date: May 5, 2014
End Date: May 9, 2014
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other

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