中国科技核心期刊

中文核心期刊

CSCD来源期刊

空间控制技术与应用 ›› 2014, Vol. 40 ›› Issue (3): 19-24.doi: 10.3969/j.issn.1674-1579.2014.03.004

• 学术研究 • 上一篇    下一篇

卫星高精度相对姿态确定技术

  

  • 出版日期:2014-06-24 发布日期:2014-08-20

A HighPrecision Relative Attitude Determination Method for Satellite

  • Online:2014-06-24 Published:2014-08-20

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.

关键词: 卫星姿态确定, 姿态角度增量, 速率陀螺, 精度

Abstract: The highresolutionimage satellite is required to achieve stringent attitude determination accuracy (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 obtained 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. Analysis and simulation results are also presented.

Key words: satellite attitude determination, attitude angular increment, rate gyro, precision

中图分类号: 

  •