星图匹配/惯性组合导航技术研究

为了多次、多点获得星光对惯性基准的误差观测量,采用了能自主识别导航星的星图匹配/惯性方案。以弹体姿态误差与陀螺漂移误差之间的关系为基础,构造了弹体姿态误差与陀螺漂移为状态量的状态方程,建立了CNS/INS组合导航模型。采用Kalman滤波技术,借助误差状态转移矩阵估计了导弹惯性基准的误差和光学陀螺的常值漂移误差。利用Matlab进行了仿真模拟,成功地实现了对导弹惯性基准误差和光学陀螺常值漂移误差的在线分离。

Research on star patterns identification/inertial integrated navigation

To obtain the error observations of inertial plane based on star sensor in different attitude,the star patterns identification/inertial integrated scheme which could autonomously identify navigation stars is adopted.According to the relationship between missile attitude error and gyro drift,the state equation which state vectors are missile attitude error and gyro drift is constructed,and the model of CNS/INS is extablished.The adaptive Kalman filter is adopted to estimate the error of missile inertial plane and the constant drift of gyro by error of state transition matrix.The using Matlab,the error of missile inertial plane and the constant drift of gyro are separated at real time successfully.