Stochastic Approach to Perform Optimal Low Thrust Spacecraft Maneuvers to Escape from Collisions

摘要

This paper considers the problem of orbital maneuvers that use a low thrust optimal control to perform orbital maneuvers in a satellite that needs to escape from a possible collision with a cloud of particles. Minimum fuel consumption is an important goal in the maneuvers considered. A version of the hybrid optimal control approach of numerically treating the problem, where one can take into account the accuracy in the satisfaction of the constraints is used. The spacecraft is assumed to be in Keplerian motion perturbed only by the thrusts. These thrusts are assumed to be of fixed magnitude and operating in an on-off mode. Numerical results are presented.