›› 2013, Vol. 33 ›› Issue (1): 30-36.doi: 10.3780/j.issn.1000-758X.2013.01.005

• 研究探讨 • 上一篇    下一篇

Halo轨道族延拓方法及特性研究

刘磊1,2,刘勇1,2,曹建峰1,2,唐歌实1,2,胡松杰1,2   

  1. (1 航天飞行动力学技术重点实验室,北京100094)(2 北京航天飞行控制中心,北京100094)
  • 收稿日期:2012-06-12 修回日期:2012-10-23 出版日期:2013-02-25 发布日期:2013-02-25
  • 作者简介:刘磊 1980年生,2010年获国防科技大学航空宇航科学与技术专业博士学位,现为北京航天飞行控制中心工程师。研究方向为深空探测轨道设计与控制。
  • 基金资助:

    国家自然科学基金(11203003),国家863计划(2011AA7034057G)资助项目

Kinetic Characteristics and Continuation Algorithm of Periodic Families

LIU Lei1,2,LIU Yong1,2,CAO Jianfeng1,2,TANG Geshi1,2,HU Songjie1,2   

  1. (1 Science and Technology on Aerospace Flight Dynamics Laboratory, Beijing 100094) (2  Beijing Aerospace Control Center, Beijing 100094)
  • Received:2012-06-12 Revised:2012-10-23 Online:2013-02-25 Published:2013-02-25

摘要: 对Halo轨道周期和运动范围等特性的研究是平动点任务设计的首要前提。针对大幅值Halo轨道和完整Halo轨道族的应用需求及其数值计算问题,面向当前应用广泛的地月系和日-地月系共线平动点,基于延拓法研究了圆型限制性三体问题下的Halo轨道族数值计算和运动学特性,给出了Halo轨道族延拓计算方法。数值仿真了族参数选择对轨道族计算的影响,得到了地月系和日-地月系共线平动点的大范围南北Halo轨道族,同时给出了轨道族的轨道周期变化和空间位置变化特性。研究结果表明,固定延拓步长下,L1点Halo轨道族应选择会合坐标系x坐标作为族参数,L2点Halo轨道族应选择y方向速度或者周期T作为族参数。方法适用于任意三体系统平动点的周期轨道族计算,特别是对其中的状态转移矩阵简单修改后可用于完整力模型下的Halo轨道(族)的数值设计。

关键词: 三体问题, 平动点, 晕轨道, 延拓法, 轨道设计, 深空探测

Abstract: Study on halo orbit period and scope of kinetic characteristics is the premise of halo orbit applications. For the applications and some numerical issues on a big halo orbit and a whole halo family, considering the wide applications of the libration points in the Sun-Earth/Moon and Earth-Moon system, the kinetic characteristics and the continuation algorithm of periodic families were studied under the circular restricted three-body problem. The method of numerical halo family determination by the continuation algorithm was presented.  Influences of family parameter selection on family determination were analyzed. Finally, the halo families with a large scope were given in the Sun-Earth/Moon and Earth-Moon system, together with their kinetic characteristics of orbit periods and locations. The results show that the family parameter of x is preferable for an L1 halo family and the y velocity or T is preferable for L2. The method is fit for the numerical halo family determination in any three-body system, especially for those under perturbations by a simple modification of state transition matrix.

Key words: Three-body problem, Libration point, Halo orbit, Continuation algorithm, Orbit design, Deep space exploration