Trajectory design for moon departure libration point mission in full ephemeris model

The lunar probe may still have some remaining fuel after completing its predefined Moon exploration mission and be able to carry out some additional scientific or technological tasks after escaping from the Moon's orbit. The Moon departure mission for the lunar probe is the focus of this paper. The possibility of the spacecraft orbiting the Moon to escape the Moon's gravitational pull is analyzed. The trajectory design for the Earth-Moon system libration point mission is studied in a full ephemeris dynamical model, which considers the non-uniform motion of the Moon around the Earth and the gravity of the Sun and planets. By applying the Particle Swarm Optimization algorithm, the trajectory design for the transfer from the Moon-centered orbit to the L1 halo orbit, the station-keeping strategies for the Earth-Moon halo orbit and the construction of homoclinic and heteroclinic orbits are investigated. Taking the tracking conditions into account, one feasible scheme for the Moon departure libration point mission for the lunar probe is presented.