Impulsive Transfer Orbit Design of NRHO for the Earth-Moon System Based on BRC4BP

This paper selected one of the Near Rectilinear HALO Orbit (NRHO) with a 9:2 resonance ratio and reduced the transmitted and orbit-insertion impulses of the transfer orbits from LEO to NRHO in the BCR4BP (Bicircular Restricted Four-Body Problem) in two steps of continuation. It is shown that the low-energy transfer orbit is mainly concentrated in the range of orbit phase 0.4∼0.6. The minimum transfer impulse is 2.892km/s. For the transfer orbits of the L2 North NRHO family, the impulse range is (2.878km/s,2.897km/s). Only 2.6 days per solar conjunction cycle are suitable for launching the probe into NRHO orbit. The optimal transfer time is in the range of 128∼130 days.