Mission trajectory design and control for spacecraft proximity relative motion

The spacecraft proximity relative motion has been a key concern in space mission design. For the target in a circular orbit, the relative motion trajectory design and control is investigated based on C-W equations, impulsive control and optimal theory. Firstly, the natural trajectory and forced trajectory are formulated by the analytical solution of C-W equations. Then, considering collision avoidance, the flyaround trajectories and local constrained trajectories are studied respectively. For the former, five trajectory modes, named natural elliptical flyaround, natural spiral flyaround, single-impulse tear-drop flyaround, multi-impulse circular flyaround and multi-impulse gymkhana flyaround, are presented. For the latter, three mission patterns named natural elliptical V-bar constrained trajectory, single-impulse R-bar constrained trajectory and multi-impulse arbitrary constrained trajectory are presented. For each trajectory pattern, the design parameters are induced by analyzing the fuel costs and process of mission. And the simulations validate the efficiency. Furthermore, the optimal models of multi-impulse circular flyaround and multi-impulse arbitrary constrained trajectory are formulated.