Design and simulation of transfer orbit for space exploration using lagrange points

For the space exploration program, it is very important to launch a satellite into a satisfactory halo orbit with the required minimum cost. This paper presents three kinds of Poincaré sections based on the invariant manifold theory, and chooses the optimal one to design the transfer orbit of Halo orbit from earth to L1 point, and analyzes the effect of parameters. The simulation results show that the lower cost transfer orbit can be designed by choosing proper Poincaré sections.