Examination of range of missions and use of atmosphere braking; 2 modes are considered, Mars orbital rendezvous with landing to be accomplished by excursion vehicle detached from parent orbiting spacecraft, and direct landing of entire spacecraft on Mars; system weights are presented in terms of number of men in crew, trip time, and stay time on Mars; chemical and nuclear propulsion is considered; chemical system is hydrogen-fluorine system with specific impulse of 450 sec; nuclear system has specific impulse of 820 sec, ratio of thrust-to-engine weight of 12, and for orbital operations thrust-to-gross weight ratio of 0.3.
Preliminary study of spacecraft for manned Mars orbiting and landing missions
SAE -- Paper
SAE Meeting ; 1964 Interplanetary
1964
11 pages
Conference paper
English
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A Preliminary Study of Spacecraft for Manned Mars Orbiting and Landing Missions
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