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 .
出处
《现代防御技术》
北大核心
2012年第1期85-89,共5页
Modern Defence Technology
关键词
主动段自旋
INS/GPS
卡尔曼滤波
命中精度
spin flight in boost phase
inertial navigation system/global position system （INS/ GPS）
Kalman filter
hit accuracy
