To cope with the problem that the transfer trajectory design for Halo orbit is difficult to convergence,and considering the background of lunar exploration,the trajectory characteristic of Halo orbit around Earth-Moon L2 point and its invariant manifolds that can reach the moon were analyzed in this paper. Then a hierarchical bisection method to design zero consumption transfer trajectory for the Halo orbit was given and the number of zero consumption transfer trajectory for all phase injection points was no more than two. Finally,an improved differential correction method including the perilune terminal condition with minimum x-axis constraint and adaptive backstepping search strategy was proposed to design transfer trajectories for all phase injection points of the Halo orbit. The simulation results indicate that the improved differential correction method has fast convergence speed and can effectively avoid the singularity,moreover it has strong adaptability and can search out transfer trajectories for all phase injection points of the Halo orbit.
