Journal of Astronautics ›› 2016, Vol. 37 ›› Issue (2): 159-168.doi: 10.3873/j.issn.1000-1328.2016.02.004

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A Design Method for Earth Moon Halo Orbit Transfer Trajectory Under Different Constraints to Moon Gravity Assisted Maneuvers

ZHANG Jing rui, ZENG Hao, LI Ming tao   

  1. 1.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
    2. Center for Space Science and Applied Research, Chinese Academy of Sciences, Beijing 100190, China
  • Received:2015-03-30 Revised:2015-09-14 Online:2016-02-15 Published:2016-02-25


To design low-energy Earth-Moon L2 Halo orbit transfer trajectory for different mission requirements, a deep research on the influence of different constraints to the moon gravity-assisted maneuvers and Halo orbit insertion (HOI) points with different amplitudes on time of flight and fuel consumption is made, and a selection strategy for HOI points is proposed in this paper. Firstly, combined with mission requirements and effects of the moon gravity, different constraints are applied to the moon gravity-assisted maneuvers. Stable manifold of Halo orbit is adjusted through differential correction algorithm and the transfer trajectory from moon to Halo orbit is designed. Then, in consideration of orbit altitude , orbit inclination, right ascension of ascending node and track angle at the same time, the hybrid optimization strategy combined genetic algorithm with differential correction algorithm is adopted to study Earth-Moon Halo orbit transfer trajectories with optimal fuel consumption. At last, the influence of moon gravity-assisted altitude and azimuth as well as different HOI points on flight time and fuel consumption of transfer trajectories is respectively analyzed, which has reference value for design and application of Earth-Moon Halo orbit transfer trajectories.

Key words: Halo orbit, Invariant manifold, Moon gravity-assisted maneuver, Hybrid optimization

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