Interim results of feasibility study presented include analytical tool for simultaneously optimizing vehicle design and its associated trajectory, typical resultant vehicle-trajectory concept, and preliminary parametric performance data; straightforward vehicle design using standard Saturn V launch vehicles is reasonably feasible; required initial mass in Earth orbit lies between 400,000 and 900,000 kg, depending on trip time, Earth return conditions, and power plant specific weight; electrical power of 3 to 8 Mw is required at power plant specific weight of 10 to 20 kg/kw.
Application of nuclear electric propulsion to manned Mars missions
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 9
1966
7 pages
Aufsatz (Zeitschrift)
Englisch
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Manned Mars landing missions using electric propulsion
NTRS | 1966
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