基于线性协方差方法的交会对接误差分析  

Error Analysis for Rendezvous and Docking with Linear Covariance Method

作　　者：王大鹏[1] 刘育强[1] 陈绍龙[1] 刘永健[1] 

机构地区：[1]中国空间技术研究院,北京100094

出　　处：《中国空间科学技术》2011年第1期48-55,共8页Chinese Space Science and Technology

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。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.

关 键 词：交会对接 误差分析 协方差 蒙特卡罗仿真 航天器 

分 类 号：V526[航空宇航科学与技术—人机与环境工程]