›› 2011, Vol. 31 ›› Issue (1): 42-47.doi: 10.3780/j.issn.1000-758X.2011.01.006

• 研究探讨 • 上一篇    下一篇

椭圆轨道相对动力学状态转移矩阵

 岳晓奎, 苑云霞   

  1. (西北工业大学航天学院,西安710072)
  • 收稿日期:2010-05-24 修回日期:2010-08-23 出版日期:2011-02-25 发布日期:2011-02-25
  • 通讯作者: 苑云霞,联系地址:陕西西安西北工业大学251信箱,邮编:710072 E-mail:mf_870125@163.com
  • 作者简介:岳晓奎 1970年生,2002年获得西北工业大学飞行器设计专业博士学位,教授,博士生导师。研究方向为航天器动力学与控制、视觉导航。
  • 基金资助:

    国家自然科学基金(10772145)

Transfer Matrix for Relative Dynamics in Elliptic Orbit

 YUE  Xiao-Kui, YUAN  Yun-Xia   

  1. (Northwestern Polytechnical University,Xi′an 710072)
  • Received:2010-05-24 Revised:2010-08-23 Online:2011-02-25 Published:2011-02-25

摘要: 针对已有研究的不足,给出了更加便于理论分析和工程应用,并具有普遍适用性的状态转移矩阵的一种新形式。基于Lawden方程推导了以三维空间中位置-速度表示的状态转移矩阵元素的具体表达式,并将其由角域变换到时域,得到了表示真实位置速度的状态转移矩阵,通过初等变换可以从该矩阵得到任意需要的形式。仿真结果表明了状态转移矩阵的有效性,可将其用于任意偏心率椭圆轨道的三维轨道交会、轨道修正、编队队形设计及控制问题。

关键词: 状态转移矩阵, 时域, 交会, 相对动力学, 椭圆轨道, 编队飞行, 航天器

Abstract: Based on Lawden equation, a new form of state transfer matrixes was presented. The state transfer matrix was derived in terms of position-velocity in solid space, and transformed from angle domain to time domain, so the state transfer matrix denoting true position and velocity was obtained. Arbitrary forms can be obtained by primary transformation. The numerical simulations show this state transfer matrix is effective and feasible for theory and project applications. It can be used for solid orbit rendezvous, orbit correction, formation configuration design and control for elliptic orbits with arbitrary eccentricity.

Key words: State-transition matrix, Time domain, Rendezvous, Relative dynamics, Elliptical orbit, Formation flight, Spacecraft