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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。
The structural deformation due to vibration during the launch of a small spacecraft or the thermal deformation of the structure caused by in-orbit solar illumination will deviate from the actual value of the focal length of the optical system calibrated by the Inertial Stellar Compass (ISC) before launch, And then affect the high-precision attitude determination of a small spacecraft, a fast on-line calibration method of ISC optical system based on attitude matrix criterion is proposed. Firstly, the mapping relationship between the focal length of the optical system and the attitude matrix is analyzed. Then, using the attitude matrix generated by the filtering at any moment and combining with the criterion of the unit orthogonality of the attitude matrix, the focal length of the ISC optical system Quick calibration online The experimental results show that the proposed method is equivalent to the pixel accuracy of the centroid extraction for the focal length of the ISC optical system, which is about 0.01 pixel. The method can calibrate the focal length of the optical system at any time in the rail, and has the advantages of fast calibration speed, no need of collecting data of a large number of attitude measurement sensors and good calibration effect.