In this paper, an optimal path planning strategy for satellite formation flying subject to the central gravity field is proposed using both high- and low-thrust based on a hybrid system approach. The hybrid optimal path planning problem is defined to find reconfiguration or rendezvous trajectories using both propulsion systems which minimize the fuel usage necessary for the maneuvers. This problem is formulated as a hybrid optimal control problem where optimal switching times between two propulsion systems and optimal control history for each system should be determined. The problem is then converted into a multi-phase optimization problem and solved by using a nonlinear optimization software named GPOPS. Numerical simulation results show that the proposed approach is more effective in terms of fuel usage than conventional high-thrust two-impulse maneuvers.
展开▼
