基于姿态矩阵判据的光学焦距在线快速标定

全伟; 刘阳; 王广君

doi:10.3788/OPE.20122005.0934

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基于姿态矩阵判据的光学焦距在线快速标定

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- 基于姿态矩阵判据的光学焦距在线快速标定
- Online fast calibration of optical focal length based on attitude matrix criterion
- 光学精密工程 2012年20卷第5期页码：934-941
- 作者机构：
  
  1. 北京航空航天大学仪器光电学院惯性技术国家级重点实验室新型惯性仪表与导航系统技术国防重点学科实验室北京,100191
  2. 中国地质大学信息技术实验中心,湖北武汉,430074
- 作者简介：
- 基金信息：
  
  国家自然科学基金资助项目(No.61004140,No.60825305,No.61104198)()
- DOI：10.3788/OPE.20122005.0934
  中图分类号： V448.2
- 收稿日期：2011-11-13，
  
  修回日期：2012-02-10，
  
  网络出版日期：2012-05-10，
  
  纸质出版日期：2012-05-10
- 稿件说明：
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全伟, 刘阳, 王广君. 基于姿态矩阵判据的光学焦距在线快速标定[J]. 光学精密工程, 2012,20(5): 934-941

QUAN Wei, LIU Yang, WANG Guang-jun. Online fast calibration of optical focal length based on attitude matrix criterion[J]. Editorial Office of Optics and Precision Engineering, 2012,20(5): 934-941
全伟, 刘阳, 王广君. 基于姿态矩阵判据的光学焦距在线快速标定[J]. 光学精密工程, 2012,20(5): 934-941 DOI： 10.3788/OPE.20122005.0934.

QUAN Wei, LIU Yang, WANG Guang-jun. Online fast calibration of optical focal length based on attitude matrix criterion[J]. Editorial Office of Optics and Precision Engineering, 2012,20(5): 934-941 DOI： 10.3788/OPE.20122005.0934.

摘要

针对在轨运行的微小航天器发射过程的振动引起的结构变形和在轨太阳光照产生的结构热变形会使发射前对惯性恒星罗盘(Inertial Stellar Compass:ISC)标定的光学系统焦距偏离实际值

进而影响微小航天器的高精度姿态确定的问题

提出了一种基于姿态矩阵判据的ISC光学系统焦距在线快速标定方法。首先

分析了光学系统焦距与姿态矩阵的映射关系;然后

利用任一时刻由滤波生成的姿态矩阵

结合姿态矩阵单位正交特性的这一判据

采用迭代法实现了ISC光学系统焦距的在线快速标定。实验结果表明:该方法对ISC光学系统焦距的标定精度同星点质心提取的像素精度相当

大约为0.01个像素。该方法可在轨随时进行光学系统焦距的标定

标定速度快

且不需要采集大量姿态测量传感器的数据

标定效果良好。

Abstract

The structure deformation of a micro-spacecraft in orbit caused by launching vibration and its thermal deformation resulted from sunlight will change the optical focal length of an Inertial Stellar Compass ( ISC) in the calibration before launching. Furthermore

it will affect on the high-precision attitude determination for the micro-spacecraft. To improve the calibration

an online fast calibration method based on the attitude matrix criterion was presented. Firstly

this method was used to analyze the mapping relation between the optical focal length and the attitude matrix. Then

combining the attitude matrix generated by the filter in any time with the orthogonal unit features of attitude matrix

the focal length of ISC was calibrated online based on an iterative method. Experimental results indicate that the calibration precision by proposed method for the optical length of the ISC system is equivalent to the extracting precision by the stellar center of mass method

and it is about 0.01 pixel. This method can calibrate the focal length at any time in orbit

and have fast calibration speeds and better calibration results without capturing a large number of other attitude measurement data from sensors.

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Keywords

references

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