System considered consists of two space vehicles namely, target vehicle (nonmaneuvering vehicle) and interceptor vehicle (maneuvering vehicle) under influence of earth gravity; interceptor vehicle has propulsive jet systems which can produce variable thrust (positive or negative) independently in three perpendicular directions; case where target vehicle is in elliptic orbit is mainly considered and some analytical difficulties involved in circular orbit case are discussed; several time-optimal trajectories for different configurations are shown. (10923)
Time-optimal rendezvous for elliptic orbits
NASA CR
NASA Contractor Reports ; n 1036
1968
114 pages
Report
Englisch
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Time-optimal rendezvous for elliptic orbits
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