Propulsion requirements for the supply of lunar-derived oxygen for a manned Mars missionThe use of lunar-derived liquid oxygen with hydrogen for robust manned explorations beyond earth is discussed. The propellant mixture ratio for optimal performance is near the current design point of r = 6. The results of NASA-sponsored studies of missions using cryogenic bipropellant H2-O2 for most functions reveal the potential benefits from a propellant terminal in cis-lunar space. The main propulsion technologies associated with Mars mission case studies include: in-space fluid transfer, zero-g ignition, oxygen-enriched propellant mixtures, throttling of main engines, and H2-O2 based auxiliary propulsion.
Document ID
19890059760
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wrobel, J. Richard (Bionetics Corp. Hampton, VA, United States)
Butterfield, Ansel J. (Bionetics Corp. Hampton, VA, United States)
Garrett, L. Bernard (NASA Langley Research Center Hampton, VA, United States)