中国空间科学技术

中国空间科学技术 ›› 2011, Vol. 31 ›› Issue (1): 48-55.doi: 10.3780/j.issn.1000-758X.2011.01.007

• 技术交流 • 上一篇    下一篇

基于线性协方差方法的交会对接误差分析

王大鹏, 刘育强, 陈绍龙, 刘永健   

  1. （中国空间技术研究院，北京 100094)
  • 收稿日期:2010-05-28 修回日期:2010-08-22 出版日期:2011-02-25 发布日期:2011-02-25
  • 通讯作者: 刘育强，联系地址：北京5142信箱93分箱，邮编：100094
  • 作者简介:王大鹏 1975年生，2005年获加拿大曼尼托巴大学机械制造工程系多学科设计与优化博士学位，高级工程师。主要从事航天器系统设计、维修性设计、结构优化设计等研究工作。 刘育强 1985年生，2010年获北京航空航天大学飞行器设计专业硕士学位，主要从事航天器系统设计、姿轨控动力学仿真等研究工作。

Error Analysis for Rendezvous and Docking with Linear Covariance Method

WANG  Da-Peng, LIU  Yu-Qiang, CHEN  Shao-Long, LIU  Yong-Jian   

  1. (China Academy of Space Technology, Beijing 100094)
  • Received:2010-05-28 Revised:2010-08-22 Published:2011-02-25 Online:2011-02-25

PDF (PC)

2601

被引次数

8

摘要： 将线性协方差分析方法和蒙特卡罗仿真相结合，按交会任务和飞行特征把交会过程分为变轨飞行、自由飞行和中途速度修正三种特征段，研究了状态误差的传播规律和交会过程中各种误差对交会对接精度的影响。在变轨飞行段，分析了追踪航天器的姿态误差、控制系统性能状态估计误差，以及目标航天器轨道摄动对状态误差传播的影响。在自由飞行段，分析了追踪航天器估计状态误差的先验值和测轨误差对状态误差传播的影响。在中途速度修正段，分析了追踪航天器姿态误差和控制系统性能误差对状态误差传播的影响。仿真结果表明，误差分析方法设计合理，可以指导交会对接的轨道设计工作，能对已经设计好的交会策略进行误差分析和设计验证。

关键词: 交会对接, 误差分析, 协方差, 蒙特卡罗仿真, 航天器

Abstract: Based on rendezvous mission and flight characteristics, a rendezvous orbit consists of three basic flight segments, i.e., orbital maneuver, free flight and midcourse velocity correction. The propagation laws of state errors and effects of errors on the accuracy of the rendezvous and docking (R&D) mission were studied with a linear covariance analysis method and Monte Carlo simulations. In the orbital maneuver segment, effects on the state error propagation caused by attitude errors, control system performance, state estimation errors of the chasing spacecraft, and orbit perturbation of the target spacecraft were studied. In the free flight segment, effects on the state error propagation caused by prior state estimation errors and orbit determination errors of the chasing spacecraft were studied. And in the midcourse velocity correction segment, effects on the state error propagation caused by attitude errors and control system performance of the chasing satellite  were studied. The results of the Monte Carlo simulations show that the proposed error analysis  method is properly designed and can be applied to the R&D orbit design and error analysis so as to validate the R&D strategy.

Key words: Rendezvous and docking, Error analysis, Covariance, Monte Carlo simulation, Spacecraft