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三颗独立的恒星获得六个观测量，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，本文所提的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 guidance of ballistic missile is a composite guidance method based on inertial guidance supplemented by starlight correction, which can significantly improve the guidance accuracy of missile. Since the star sensor is strapdown mounted on the missile body, the installation error will affect the accuracy of stellar meas-urement and the precision of composite guidance. Thus a composite guidance method for on-line identification and correcting the star sensor installation error is proposed. The relationship between the observed amount of star sensor and platform misalignment angle and 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 star sensor installation error can be estimated by the least square method. Finally, optimal correction factor determination equation of stellar-inertial composite guidance is improved, and the influence of star sensor installation error is corrected directly. The simulation results show that the proposed approach can estimate the plat-form misalignment angle and the star sensor installation error effectively. The precision of strapdown stellar -inertial composite guidance is improved.
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