Optimum thrust programs are used to generate rendezvous trajectories from Earth to Mars for various flight times and launch dates during years 1968 to 1971; manner in which propulsion requirements vary with flight time and launch date is considered; comparison of vehicle performance using variable and constant thrust programs; existence of optimum launch dates is interpreted in terms of certain transversality conditions derivable from calculus of variations; comparison of advanced propulsion and ballistic vehicle propulsion requirements for Earth-Mars rendezvous trajectories.
Optimum interplanetary rendezvous with power-limited vehicles
AIAA J
AIAA Journal ; 1 , n 1
1963
7 pages
Article (Journal)
English
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