现代防御技术2012，Vol.40Issue(1)：85-89,5.DOI:10.3969/j.issn.1009-086x.2012.01.018
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
摘要
Abstract
Spin flight of ballistic missile in boost phase may penetrate laser' s interception. However, it will induce errors of speed and position. And it also induces biggish impact point deviation. A scheme about correcting point deviation by INS/GPS combined guidance in free phase is put forward. Spin mode of boost phase is based at first and speed error, position error and final point deviation induced by spinning in boost phase are analyzed. Then INS/GPS combined guidance method is 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Key words
spin flight in boost phase/inertial navigation system/global position system ( INS/ GPS)/Kalman filter/hit accuracy分类
军事科技引用本文复制引用
魏鹏涛..INS/GPS组合制导修正主动段自旋误差研究[J].现代防御技术,2012,40(1):85-89,5.
