中文摘要：

研究地球静止轨道卫星的扫描镜运动补偿问题,以消除卫星姿态偏差和扫描镜法线偏移引起的光轴指向偏差.给出了带有两自由度扫描镜的航天器姿态动力学方程以及光轴指向误差的描述.以欧拉角描述卫星姿态,以欧拉轴/角参数来描述扫描镜法线偏移,并推导了这2种影响因素对光轴指向的误差传递关系.针对法线偏移不易测量的特点,利用扫描镜在特定工作模式下的准确定向能力和法线偏移的长周期特性,给出了一种偏移参数的估计算法,每隔一定的时间段对法线偏移估计值进行更新.在此基础上给出了一种基于卫星姿态和法线偏移信息的运动补偿算法,对扫描镜的扫描角和步进角分别进行补偿.数值仿真结果验证了补偿算法的有效性.

英文摘要：

The problem of mirror motion compensation was studied for a geostationary satellite to eliminate the optical axis direction deviation due to attitude deviation and normal line deviation of the mirror. The rotational dynamical equation of a spacecraft with two-degree freedom scan mirror was presented. The satellite atti- tude was described by Euler angles, and the normal line deviation of the mirror was described by Euler axis/ angle parameters. The error transfer function from the two influencing factors to the optical axis direction was deduced. To resolve the problem of immeasurability of the normal line deviation, an estimation algorithm was presented using the precise direction finding ability of the scan mirror during special operation mode, and the long period character of the normal line deviation. The estimated value of the normal line deviation was replaced at set time intervals. Based on the estimation algorithm, a compensation algorithm was presented using the information of satellite attitude and normal line deviation, which compensated the scanning angle and the stepping angle separately. Numerical simulation results demonstrate the validity of the compensation algorithm.