Design of Transfer Trajectories between Earth-Moon L1 and L2 Libration Points in the Ephemeris Model

Aiming at the problem of designing transfer orbits between the Earth-Moon libration points L1 and L2, this paper proposes a transfer orbit design method based on a high-precision dynamic model. The research uses a linear difference correction algorithm to realize the full correction of orbit parameters under a high-precision ephemeris model and designs a family of shuttle orbits with adjustable Z-axis amplitude for the Earth-Moon L2 point Halo orbit. Experiments show that this family of orbits exhibits quasiperiodic oscillation characteristics of 32-34 days in a real perturbation environment, and the orbit maneuver velocity increment is stable in the range of 0.5-0.7 m/s. Among them, the ultra-low energy consumption of the order of 0.5 m/s verifies the engineering applicability of the weak stability boundary theory. The shuttle orbit proposed in the research has both quasiperiodic maintenance capability and microamplitude control characteristics, providing an orbit switching scheme with both low energy consumption and high precision for deep space exploration missions, and has important application value for complex mission configurations such as multi-target cooperative exploration and orbit reconstruction.