Study of propulsion requirements for lunar orbiting and landing missions, including requirements imposed by flight paths, accelerometer errors, altitude determination errors, and impulse errors, with attention to minimizing number of maneuvers, number of engines, and throttling requirements; single fixed-thrust engine will satisfy requirements for orbiting mission; for landing from lunar orbit, single regeneratively cooled engine with throttling range as low as 3.5 to 1 appears acceptable; if system has separate landing engine, throttling range as low as 2 to 1 appears acceptable.
Spacecraft propulsion requirements for lunar missions
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 2 , n 1
1965
8 pages
Aufsatz (Zeitschrift)
Englisch
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