Construction of the return trajectory to the neighborhood of the collinear libration point of the Sun–Earth system
Special type of maneuvering of a spacecraft in the Earth space is investigated. The type is associated with the return to the neighborhood of the collinear libration point L1. The Hill problem of the circular restricted three body problem of the Sun–Earth system is considered. These trajectories are determined by the “hazard function” which is a special linear form of a phase coordinates. Resulting conditions of the return are used to construct the corrective control. An algorithm for construction of the “return trajectory” in the neighborhood of the collinear libration point is proposed. The results of the numerical integration are graphically illustrated.