Minimum fuel trajectory design using sparse optimal control in three-body problem

This study formulates a successive multiple sparse optimal control method to minimize a fuel consumption of spacecraft in three-body problem. This method uses a convex optimization under linearlized dynamics, however it enables to find an optimal solution that satisfies a nonlinear dynamics by successive convexification. Furthermore, the divergence of the state constraint due to the instability of the three-body system can be avoided by dividing the state constraint into several sections. This method is applied to a transfer from Near Rectilinear halo orbit (NRHO) to Low lunar orbit (LLO) in the Earth-Moon system.