考虑星敏感器安装误差的弹道导弹捷联星光/惯性复合制导

弹道导弹捷联星光/惯性制导是在惯性制导基础上辅以星光修正的一种复合制导方法，能够显著提高导弹制导精度。由于星敏感器捷联安装在弹体上，安装误差会影响恒星测量的精度，进而影响复合制导精度，为此提出一种在线辨识并修正星敏感器安装误差的复合制导方法。建立了星敏感器观测量与数学平台失准角、星敏感器安装误差的关系方程，在导弹主动段关机后测量3颗独立的恒星获得6个观测量，利用最小二乘法估计出失准角和星敏感器安装、误差。改进了星光/惯性复合制导的最佳修正系数确定方程，直接修正了星敏感器安装误差的影响。数值仿真结果表明：所提方法可以有效地估计平台失准角和星敏感器安装误差，提高了捷联星光/惯性复合制导的精度。

Strapdown stellar-inertial composite guidance method for ballistic missiles considering star sensor installation errors

Strapdown stellar-inertial guidance of ballistic missiles is a composite guidance method based on inertial guidance supplemented by starlight correction. It can significantly improve the guidance accuracy of missiles. However, since the star sensor is strapdown mounted on the missile body, installation errors will inevitably affect the accuracy of stellar measurement and the precision of composite guidance. Therefore, a composite guidance method for on-line identification and correction of the star sensor installation errors is proposed. The relationship among the observations of the star sensor, the platform misalignment angle, and the star sensor installation error is established. After the active segment of the missile is shut down, six observations are obtained by measuring three independent stars. The misalignment angle and the star sensor installation error can be estimated by the least square method. The optimal correction factor determination equation of the stellar-inertial composite guidance is improved, and the influence of the star sensor installation error is directly eliminated. The simulation results show the effectiveness of the proposed approach in estimating the platform misalignment angle and the star sensor installation error, thus improving the precision of the strapdown stellar-inertial composite guidance.