A series of simulated manned Mars missions was analyzed by a computer model. Numerous mission opportunities and mission modes were investigated. Sensitivity trade studies were performed of the vehicle all-up mass and propulsion stage sizes as a function of various levels of conservatism in mission velocity increment margins, payload mass and propulsive stage characteristics. The longer duration but less energetic type of conjunction class mission is emphasized. The specific mission opportunity reviewed was for a 1997 departure. From the trade study results, a three and one-half stage vehicle concept evolved, utilizing a Trans-Mars Injection (TMI) first stage derived from the Space Shuttle External Tank (ET).
Manned MARS Mission Concept with Artificial Gravity
1986
14 pages
Report
No indication
English
Manned Spacecraft , Artificial gravity , Computerized simulation , Manned space flight , Mars (Planet) , Spacecraft configurations , Spacecraft propulsion , Trajectory analysis , External tanks , Long duration space flight , Mathematical models , Mission planning , Multistage rocket vehicles , Payload mass ratio , Spacecraft environments , Spacecraft modules
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