INS/GPS组合制导修正主动段自旋误差研究  

Research on Boost Phase Spinning Error Correction by INS/GPS Combined Guidance Method

作　　者：魏鹏涛 

机构地区：[1]第二炮兵工程大学,陕西西安710025

出　　处：《现代防御技术》2012年第1期85-89,共5页Modern Defence Technology

摘　　要：弹道导弹主动段自旋可以对抗激光武器拦截,实现主动段突防。但是主动段自旋又会引起较大的速度位置偏差,进而造成较大的落点偏差。提出了一种通过自由段组合制导修正落点偏差的方案。首先建立了主动段自旋弹道模型,分析了主动段自旋引起的速度位置误差及最终的落点偏差,然后在自由段采用INS/GPS组合制导,应用卡尔曼滤波对数据进行处理。仿真表明,该方法可以明显提高导弹的命中精度。Spin flight of ballistic missile in boost phase may penetrate laser＇ s interception it will induce errors of speed and position. And it also induces biggish i about correcting point deviation by INS/GPS combined guidance in free of boost phase is based at first and speed error, position error and final ning in boost phase are analyzed. Then INS/GPS combined guidance me mp ph act point deviation. However, A scheme ase is put forward. Spin mode poin thod t deviation induced by spinis adopted in free phase and the INS/GPS Kalman Filter mode is applied. The simulation indicates that this method can improve the hit accuracy of missile clearly .

关 键 词：主动段自旋 INS/GPS 卡尔曼滤波 命中精度 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] P228.4[天文地球—大地测量学与测量工程]