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1.By means of temporary stability of combining drift coefficient of angle sensor and through missile rotating two-position measurement, measuring rotating angle between the two positions by vertical sensitive axis X, and sensing the changes of ground velocity component between the two positions by horizontal sensitive axis γ and z, the position of the component is determined to realize the azimuth alignment before launch of tactical missile.
角敏感元件漂移系数具有短期稳定性，通过转弹前后两位置对组合的测试，垂直敏感轴计测转弹过程中两位置之间的转角，两水平敏感轴敏感计测地速分量在前后两位置的变化，由此计算出部件当前所在方位，从而实现战术弹射前的方位对准。收藏指正
2.SINS Nonlinear Alignment with Large Azimuth Misalignment Angles
捷联惯导系统大方位失准角下的非线性对准收藏指正
3.INS Nonlinear Alignment with Large Azimuth Misalignment Angle Using Predictive Filter
预测滤波器理论在惯导非线性对准中的应用收藏指正
4.The INS nonlinear alignment with a large azimuth misalignment angle using predictive filter is discussed in this paper. In order to deal with the problem that the gyro errors are non-observable, an improved algorithm combining predictive filters and extended Kalman filters is proposed.
讨论了预测滤波器的基本算法,并针对平台惯性导航系统在大方位失准角情况下的非线性对准中,用预测滤波器无法估计陀螺误差的问题,提出了将预测滤波和扩展卡尔曼滤波相结合的算法。收藏指正
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