AIAA Journal · 1963 · 45 citations · 5 references
EngineeringAerospace EngineeringOrbital MechanicsPropulsionSpacecraft DesignInterplanetary TrajectoriesOrbital ManeuversPropulsion SystemsSpacecraft Trajectory DesignTrajectory OptimizationVehicle Propulsion SystemsFlightInterplanetary Trajectory DesignInterplanetary Trajectory OptimizationPropulsion System RequirementsRendezvous Trajectory DesignSpacecraft Rendezvous DynamicsSpacecraft Trajectory OptimizationTime Of Flight
The optimum thrust programs for power-limited propulsion systems are used to generate rendezvous trajectories from Earth to Mars for various flight times and launch dates during the years 1968 to 1971. The manner in which the propulsion requirements vary with flight time and launch date is considered, and a comparison of vehicle performance using the variable and constant thrust programs is presented. The existence of optimum launch dates is interpreted in terms of certain transversality conditions derivable from the calculus of variations. A brief comparison of the advanced propulsion vehicle and the ballistic vehicle propulsion requirements is made for Earth-Mars rendezvous trajectories.
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Optimum low-thrust rendezvous and station keeping
T. N. Edelbaum · AIAA Journal · 1964 · 90 citations
Optimum power-limited orbit transfer in strong gravity fields
T. N. Edelbaum · 1964 · 67 citations
Researches in Interplanetary Transfer
J. V. Breakwell, ROLLIN W. GILLESPIE, Stanley E. Ross · ARS journal · 1961 · 38 citations