Accessible Domain of Cislunar Space for Halo Orbits at the Earth-Moon L1 Lagrange Point

To address the problem of evaluating the cislunar accessibility of spacecraft operating on Halo orbits around the Earth-Moon L1 libration point, this study adopted the circular restricted three-body problem as the dynamical model and designed transfer trajectories using invariant manifolds. All feasible transfer schemes were efficiently solved by combining coarse traversal search and refined sampling search. The accessible regions and maneuver energy consumption characteristics of Halo orbits with different Jacobi constants for the 200 km altitude lunar orbit were quantitatively analyzed. The results show that the accessible regions of Halo orbits corresponding to different Jacobi constants are complementary, enabling the large-scale coverage of cislunar space, and that an optimal transfer phase exists to minimize both the velocity increment and transfer time.