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Propulsion systems using in situ propellants for a Mars Ascent VehicleThe indigenous propellants of oxygen and carbon monoxide were studied for use in a Mars Ascent Vehicle (MAV). Both the oxygen and carbon monoxide were evaluated as turbine working fluids for a full expander engine cycle used in the MAV. Two oxygen working fluid engines and four carbon monoxide engines were investigated. The maximum hot-gas-side wall temperature was limited to either 445 K (800R) or 556 K (1000 R) over a range of working fluid mass flows. An engine thrust of 44.5 kN (1,000 lb(sub f)) was assumed. The engine characteristics of coolant inlet pressure, total engine length, specific impulse, pump efficiencies, and turbine power required were optimized. Of the six engines evaluated, the study showed that either type of working fluid was feasible for a MAV engine. Using carbon monoxide as the working fluid resulted in the best engine characteristics.
Document ID
19920066377
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wadel, Mary F.
(NASA Lewis Research Center Cleveland, OH, United States)
Roncace, Elizabeth A.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 92-3445
Accession Number
92A49001
Distribution Limits
Public
Copyright
Other

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