弹道导弹SINS空中在线标定方法

An In-flight Calibration Method of Ballistic Missile SINS

从工程应用的角度出发,利用高精度的GPS信息,研究了一种弹道导弹捷联惯导系统(SINS)空中在线标定方法,建立了发射点惯性系下SINS的误差模型,应用分段线性定常系统(PWCS)的可观测性分析理论和奇异值方法,定量地研究了系统状态变量的可观测度。针对SINS初始失准角及惯性器件误差所造成的导航误差,利用弹载GPS得到的速度和位置量测信息,通过最优估计的方法标定出SINS的导航误差,并采用误差状态转移算法反推初始平台失准角,从而为导弹的后续飞行提供精确的惯性器件误差系数和姿态基准。通过仿真验证了弹道导弹SINS空中在线标定方法的正确性和可行性。

Based on the engineering utility, an in-flight calibration method is presented in order to realize the on-line estimation and compensation for the ballistic missile strapdown inertial navigation systems （SINS） by using GPS velocity and position information. The error model of SINS is established, and the observability of state variables is quantitatively studied by means of the observability analysis theory of piece-wise constant caused by initial mi system （PWCS） and the singular value decomposition. Aimed at the navigation errors salignment angle and inertial sensor errors, a novel scheme is proposed by using the GPS information to update SINS. Through the utilization of optimum theory and transmission matrix, the navigation errors and initial misalignment are acquired to provide the attitude reference and sensor errors of SINS for the following flight. Finally, the simulation results show the validity of the in-flight calibration method of ballistic missile.