Cryogenic propellant thermal control system design considerations, analyses, and concepts applied to a Mars human exploration mission

Details Cryogenic propellant thermal control system design considerations, analyses, and concepts applied to a Mars human exploration mission Cryogenic propellant thermal control system design considerations, analyses, and concepts applied to a Mars human exploration mission

Jun 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993jpmc.confqs...p&link_type=abstract

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 17 p.

Mathematics

Logic

Control Systems Design, Cryogenic Rocket Propellants, Manned Mars Missions, Specific Impulse, Temperature Control, Thermal Analysis, Cryogenic Fluid Storage, Nasa Space Programs, Propulsion System Performance, Space Exploration, Technological Forecasting

Scientific paper

This paper analyzes, defines, and sizes cryogenic storage thermal control systems that meet the requirements of future NASA Mars human exploration missions. The design issues of this system include the projection of the existing Multilayer Insulation data base for cryogenic storage to much thicker (10 cm or more) insulation systems, the unknown heat leak from mechanical interfaces, and the thermal and structural performance effects of the large tank sizes required for a Mars mission. Acknowledging these unknown effects, heat loss projections are made based on extrapolation of the existing data base. The results indicate that hydrogen, methane, and oxygen are feasible propellants, and that the best suited thermal control sytems are 'thick' MLI, thermodynamic vent sytems, cryocoolers, and vacuum jackets.

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