Explicit space guidance scheme, which combines phasing and propellant advantages of parking orbits with rapid response time of direct ascent, is described; resulting flight plans yield multiburn trajectories spanning continuum from direct ascent (2-burns) to parking orbit approaches (4 or more burns); onboard computer selects automatically and continuously flight plan depending on instantaneous geometry; system reaction time to arbitrary mission situation is measured in seconds; results of computer sizing study are presented, showing that scheme can be implemented in aerospace computer; scheme, developed for satellite rendezvous, is applicable to emergency rescue missions or any mission requiring injection of payloads into precise Earth orbits.
Variable point guidance for space missions
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 8
1966
8 pages
Article (Journal)
English
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