Optimal Planetary Orbital Transfers via Chemical Engines and Electrical Engines

摘要

Because the orbital periods for planetary orbital transfers are of order hour, the primary objective of an optimal trajectory is to minimize the propellant consumption. In this paper, we present a systematic investigation of optimal trajectories for planetary orbital transfer. Major results on thrust control, propellant consumption, and flight time are presented with particular reference to LEO-to-GEO transfer. The following results were obtained with the sequential gradient-restoration algorithm in either single-subarc form or multiple-subarc form: For minimum propellant consumption, the thrust direction is tangent to the flight path. The thrust magnitude has a three-subarc form: powered flight with maximum thrust is followed by coasting flight, which is followed by powered flight with maximum thrust.