Research on Transfer Orbit Based on Electric Propulsion Satellite to Halo Orbit

Energy-saving optimization was achieved by using the characteristics of low-thrust electric propulsion and the orbital dynamics. The transfer orbit of the spacecraft from the Earth parking orbit to the Sun-Earth L2 point Halo orbit has been studied by combining the invariant manifold in the restrictive three-body problem with the low thrust trajectory optimization. Firstly, the transfer orbit is divided into burn and coast phases. Tangential acceleration was used to decrease Jacobi integration constant rapidly, and then Radau pseudo spectral method was adopted in the burn phases to optimize the orbit so that the spacecraft could reach the stable invariant manifold of the target orbit. When the spacecraft reached stable invariant manifold, it could coast to target halo orbit. The initial transfer orbit was guessed by Jacobi integration constant. Finally, a simulation example of transfer orbit was given to verify the effectiveness of the method. The results show that it is of guiding significance to practical engineering application.