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Propellant Gauging for ExplorationThis paper presents a brief overview of propellant gauging needs and requirements in the context of lunar exploration missions defined by the Exploration Systems Architecture Study (ESAS) report. A timeline for the development and testing of gauging technologies, and a few key design review dates are presented. A lunar exploration mission scenario is discussed which aids in defining the propellant gauging needs. The fleet of new exploration vehicles includes the Ares I and Ares V launch vehicles, Earth Departure Stage (EDS), Lunar Surface Access Module (LSAM) ascent and descent stages, and the Orion Crew Exploration Vehicle (CEV). The liquid propellant choices are currently oxygen - hydrogen for the launch vehicles, the EDS, and LSAM descent module; oxygen - methane for LSAM ascent module; and monomethylhydrazine nitrogen tetroxide (MMH-NTO) for the CEV. Estimated tank sizes, temperatures, pressures, and storage durations are presented. A baseline propellant gauging system is proposed that is based on high Technology Readiness Level (TRL) gauging technologies. In order to be considered for use on the new exploration vehicles, any new gauging technologies will have to show a clear benefit over the baseline methods in terms of performance and/or cost.
Document ID
20070022411
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Zimmerli, Gregory A. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 23, 2013
Publication Date
May 14, 2007
Subject Category
Lunar And Planetary Science And Exploration
Meeting Information
Meeting: 54th JANNAF Propulsion Meeting
Location: Denver, CO
Country: United States
Start Date: May 14, 2007
End Date: May 19, 2007
Sponsors: Department of the Army, NASA Headquarters, Department of the Air Force, Department of the Navy
Funding Number(s)
WBS: WBS 253225.04.01.02.05.03.03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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