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为提高轨道几何状态惯性检测系统姿态精度,提出一种零速姿态修正方法,利用轨道几何状态惯性检测系统载体系横向及垂向速度为0的先验条件,构造Kalman滤波横向及垂向观测量。选用HT-50M型激光陀螺仪和JN-06A型石英挠性加速度计组成惯性导航系统,并进行现场检测试验。结果表明:在轨检仪连续工作300m情况下,零速姿态修正方法能够有效抑制惯性导航系统姿态误差增长,轨道检测精度提高2倍。
In order to improve the attitude accuracy of inertial detection system of orbital geometry, a zero-speed attitude correction method is proposed. By using the prior condition that the vertical and horizontal velocities of the system are zero, the horizontal and vertical Kalman filtering . The HT-50M laser gyro and the JN-06A quartz flexible accelerometer were used to compose the inertial navigation system, and the on-site testing was conducted. The results show that the zero-speed attitude correction method can effectively restrain the growth of attitude error of inertial navigation system and improve the accuracy of orbit detection by twice.