中国物理B ›› 2008, Vol. 17 ›› Issue (1): 350-355.doi: 10.1088/1674-1056/17/1/061

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Optimized transfer trajectories in the earth--moon system

蔡力1, 谢文贤2, 徐伟2   

  1. (1)College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China; (2)School of Science, Northwestern Polytechnical University, Xi'an 710072, China
  • 出版日期:2008-01-20 发布日期:2008-01-20
  • 基金资助:
    Project supported by the National Natural Science Foundation of China (Grant Nos 10472091 and 10332030).

Optimized transfer trajectories in the earth--moon system

Xie Wen-Xian(谢文贤)a)†, Xu Wei(徐伟)a), and Cai Li(蔡力)b)   

  1. a School of Science, Northwestern Polytechnical University, Xi'an 710072, China; b College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
  • Online:2008-01-20 Published:2008-01-20
  • Supported by:
    Project supported by the National Natural Science Foundation of China (Grant Nos 10472091 and 10332030).

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摘要： Investigations of low energy transfer trajectories are important for both celestial mechanics and astronautics. Methodologies using the theories from dynamical systems are developed in recent years. This paper investigates the dynamics of the earth--moon system. Low energy transfer trajectories are solved numerically by employing a hybrid strategy: first, a genetic hide and seek method performs a search in large domain to confine the global minimum $f({\eta})$ (objective function) region; then, a deterministic Nelder--Mead method is utilized to refine the minimum quickly. Some transfer trajectories of the spacecraft in the earth--moon system are successfully simulated which verify the desired efficiency and robustness of the method of this paper.

关键词: celestial mechanics, dynamical astronomy, orbit

Abstract: Investigations of low energy transfer trajectories are important for both celestial mechanics and astronautics. Methodologies using the theories from dynamical systems are developed in recent years. This paper investigates the dynamics of the earth--moon system. Low energy transfer trajectories are solved numerically by employing a hybrid strategy: first, a genetic hide and seek method performs a search in large domain to confine the global minimum $f({\eta})$ (objective function) region; then, a deterministic Nelder--Mead method is utilized to refine the minimum quickly. Some transfer trajectories of the spacecraft in the earth--moon system are successfully simulated which verify the desired efficiency and robustness of the method of this paper.

Key words: celestial mechanics, dynamical astronomy, orbit

中图分类号:  (Celestial mechanics (including n-body problems))

  • 95.10.Ce
95.75.Pq (Mathematical procedures and computer techniques) 96.20.Br (Origin and evolution)