摘要
首先讨论了卫星姿态确定原理的建模问题,针对星敏感器/陀螺组合配置的定姿系统,详细分析了动态滤波算法原理,推导了星敏感器观测矩阵及误差四元数状态方程,进而建立了使用Kalman滤波方法进行姿态确定的整个过程;并基于该滤波算法,讨论了姿态确定系统的最终定姿精度的分析与综合评估问题,从理论分析和仿真验证两方面确定了影响姿态确定精度的主成分误差因素,定量描述了误差因素的影响范围,并针对实际工程指标完成了主成分因素的边界条件,为姿态测量方案的设计提供了理论支撑。
The principle modeling on satellite attitude determination was discussed firstly.Aiming at the combined system composed of star sensor and gyro,the principle of dynamic filter algorithm was analyzed and the error state equation,measurement equation as well as measurement matrix were deduced;and moreover the process flow to realize attitude determination by dynamic Kalman filter was established.Secondly,based on this filter algorithm,the analysis and integrative evaluation for the finial attitude determination precision in this combined system were discussed,in which the principal componential error factors to influence attitude determination precision were validated both from theory analysis and simulation experiment,and then the influence coverage of error factor was depicted quantificationally;finally,the boundary condition of principal components was obtained according to the actual engineering indexes,which all can provide theoretical support for the design of attitude measurement schemes.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2009年第23期7408-7412,7417,共6页
Journal of System Simulation
基金
国家自然科学基金(60272013)
航天支撑技术基金项目(GFKD-HT-2006-02)
关键词
姿态确定
原理建模
KALMAN滤波
精度因子
边界条件
Attitude determination
principle modeling
Kalman filter
precision factor
boundary condition
