卫星高精度相对姿态确定技术  

A High-Precision Relative Attitude Determination Method for Satellite

作　　者：张春青[1,2] 王淑一[1,2] 陈超[1] 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术重点实验室,北京100190

出　　处：《空间控制技术与应用》2014年第3期19-24,共6页Aerospace Control and Application

基　　金：高分辨率对地观测系统重大专项青年创新基金(GFZX04060103)资助项目

摘　　要：高分辨率遥感卫星姿态事后处理精度的典型指标要求为2.4″(3σ).受星敏感器低频误差影响,常规的星敏感器/陀螺组合定姿方法的姿态确定精度难以实现上述指标要求.考虑到陀螺短期测量精度高的特性,提出了一种基于陀螺测量信息的相对姿态确定方案.利用陀螺信息确定各时刻相对于起始时刻的相对姿态,起始时刻的绝对姿态精度由地面高精度标定等手段保证.采用该方案可以在一定时间内实现高精度的姿态确定精度.给出了针对该方案的理论分析、数学仿真以及物理仿真试验结果.The high-resolution-image satellite is required to achieve stringent attitude determination accu- racy 2.4″（3σ） ground-based） in order to provide precise geometric accuracy. Influenced by the star sensor＇ s low frequency error （LFE）, the conventional star sensors/gyros attitude determination system cannot achieve the precision requirement. For this reason, a new method for accurate attitude estimation with gyro-based reference time is proposed, and the satellite attitude estimates at the reference time is ob- tained on the ground by using the ground control points. The most relative time for achieving the required precision is limited because the effect of gyro＇ s bias errors and drifts is very significant in long term. A- nalysis and simulation results are also presented.

关 键 词：卫星姿态确定 姿态角度增量 速率陀螺 精度 

分 类 号：V44[航空宇航科学与技术—飞行器设计]