Indirect Optimization of Low-Thrust Capture Trajectories

Abstract

The theory of optimal control is used to find the best trajectories for the capture maneuver of an interplanetary probe, which employs electric propulsion. The thrust magnitude and direction are optimized to exploit the spacecraft continuous steering capabilities and maximize the spacecraft final mass. Strategies, which involve propelled and coast arcs, are analyzed. The influence on the optimal trajectories of some parameters, such as the thrust, the specific impulse, and the initial velocity, is also discussed