›› 2014, Vol. 34 ›› Issue (2): 69-75.doi: 10.3780/j.issn.1000-758X.2014.02.009

• 技术交流 • 上一篇    下一篇

编队飞行相对倾斜构形的e/i 矢量控制方法

 伍升钢1,2, 钱山1,2, 李恒年1, 谭,1,2   

  1. (1宇航动力学国家重点实验室,西安710043) (2中国西安卫星测控中心,西安710043)
  • 收稿日期:2013-06-28 修回日期:2013-10-25 出版日期:2014-04-25 发布日期:2014-04-25
  • 作者简介:伍升钢 1983年生,2008年获国防科学技术大学航天与材料工程学院力学专业硕士学位。主要研究方向为航天器轨道最优控制。

Control Method Based On e/i Vector to Realize Satellites Formation with Relative Inclined Configuration

 WU  Sheng-Gang1,2, QIAN  Shan1,2, LI  Heng-Nian1, TAN  Wei1,2   

  1. (1StateKeyLaboratoryofAstronauticDynamics,Xi′an710043)
    (2Xi′anSatelliteControlCenter,Xi′an710043)
  • Received:2013-06-28 Revised:2013-10-25 Online:2014-04-25 Published:2014-04-25

摘要: 针对分布式卫星编队飞行相对倾斜构形设计与控制问题进行了研究,提出了基于e/i矢量相对运动模型的相对倾斜构形设计算法,给出了相对倾斜构形与偏心率偏差、轨道倾角偏差和升交点赤经偏差的关系,并针对相对倾斜构形偏置量的特点,提出了基于高斯摄动方程编队控制模型的一种四脉冲构形捕获控制算法,仿真结果表明,以e/i 矢量进行构形设计,方法直观,捕获控制策略简单,绕飞构形稳定。

关键词: 分布式卫星, e/i矢量, 相对倾斜构形, 绕飞角, 轨道控制

Abstract: The problem of relative inclined configuration design and orbit control of the distributed InSAR satellites formation flying was studied. First, the algorithm of relative inclined configuration design based on e/i vector was put forward. Then the relationship between the relative inclined configuration and the errors of eccentricity, inclination and the right ascension of ascending node were given.According to the properties of relative inclined configuration of distributed satellites, the four impulse orbit maneuver strategy was put forward based on the Gauss perturbation functions satelliteformation control model. Simulation results show that the method of relative inclined configuration design is intuitionistic, the orbit maneuver strategy is simple and the configuration is stable.

Key words: Distributed satellites, e/i vector, Relative inclined configuration, Flying-around angle, Orbit control