摘要
给出利用星敏感器进行惯性姿态和对地姿态确定的流程,重点分析了惯性姿态向对地姿态转换过程中的误差传播关系,给出了相应的误差传播矩阵和误差传播影响因子.仿真表明,由于坐标转换时引入轨道参数误差,误差传播影响因子一般在1～2之间,因而使得对地定姿精度较惯性定姿精度稍低。
The determination flow for inertial attitude and orbit coordinate system attitude using star sensors is presented. Accuracy analysis for the orbit coordinate system attitude is discussed in detail, and the error propagation relationship between the inertial attitude and the orbit coordinate system attitude is studied. The error propagation matrix and the error propagation influence factor are defined. Simulation shows that the factor usually ranges from 1 to 2, which leads to the result that the accuracy of the orbit coordinate system attitude is comparatively worse than that of the inertial attitude because of the influence of orbit parameter error during coordinate conversion.
出处
《飞行器测控学报》
2006年第5期27-31,共5页
Journal of Spacecraft TT&C Technology
基金
国家自然科学基金（No.60402033）资助项目
关键词
星敏感器
精度分析
对地姿态
坐标转换
Star Sensor
Accuracy Analysis
Orbit Coordinate System Attitude
Coordinate Conversion
