一种航天器姿态控制系统多源误差分析方法

A multi-source error analysis method for spacecraft attitude control system

针对航天器姿态高精度控制问题,建立了一套完整的航天器姿态控制系统误差传播动态分析流程。首先,进行航天器姿态控制系统的误差来源分析,提出敏感器、执行器等的通用误差建模方法,将不确定度以可量化分析的形式引入误差传播分析。然后,使用线性化协方差分析和基于奇异值分解(SVD)的改进无迹变换协方差分析方法,对姿态控制系统误差传播进行动态分析。最后,仿真验证了所提方法的精度,并进行了误差传播分析。仿真结果表明,所提方法能够分析误差源单独作用和综合作用下误差传播的动态特性,并且在保证分析精度的前提下显著提升了计算效率。

Focusing on high-precision control of spacecraft attitude,a complete error propagation chain dynamic analysis process for the spacecraft attitude control system was established.Firstly,the error sources of the spacecraft attitude control system were analyzed,and further proposed a univer-sal error modeling method for the measurement model and output model of sensors and actuators.Uncertainty was introduced into the error propagation chain in the form of quantifiable analysis.Then,using linearized covariance analysis and the improved unscented transform covariance analysis method based on SVD decomposition,the error propagation chain of the attitude control system was dynamically analyzed.Finally,the accuracy of the proposed method was verified by simulation tests and the error propagation was analyzed.The simulation results show that the proposed method can analyze the dynamic characteristics of the error propagation chain under the action of different error sources,and significantly improve computational efficiency while ensuring analysis accuracy.