摘要
以无控多管火箭制导化改造过程中弹载子惯导初始对准问题为背景,研究了利用火箭发射车高精度惯性导航系统作为主惯导,对多管火箭弹载子惯导同时进行传递对准的方案。详细推导了利用主、子惯导输出的姿态信息构造传递对准Kalman滤波量测方程。数学仿真结果表明,采用姿态匹配传递对准方案,仅利用多管火箭发射过程正常的俯仰、回转机动,在20 s内就能实现对弹载子惯导的初始对准和射前标定,对准精度达角分级,为提高制导型多管火箭发射精度提供了一种可行的思路。
As the range of a free-flight rocket increases,so do the delivery errors.Using position and azimuth determining system of GMLRS as Master Inertial Navigation System（MINS）,the attitude matching transfer alignment is applicated to determine initial attitudes of missile-borne Slave Inertial Navigation Systems（SINS） simultaneously.Kalman filter based on the attitude information of MINS and SINS is presented.Simulation result show that the Kalman filter for the attitude matching transfer alignment can accomplish the task in about 20 s to the accuracy of minute level.
出处
《压电与声光》
CSCD
北大核心
2010年第4期565-567,共3页
Piezoelectrics & Acoustooptics
基金
武器装备预研基金资助项目(9140A09051206HK0342)
