| INS/GPS组合制导修正主动段自旋误差研究 |
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| 引用本文： | 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. |
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| 作者姓名： | 魏鹏涛 |
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| 作者单位： | 第二炮兵工程大学,陕西西安,710025 |
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| 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.
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| 关 键 词： | 主动段自旋 INS/GPS 卡尔曼滤波 命中精度 |
Research on Boost Phase Spinning Error Correction by INS/GPS Combined Guidance Method |
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| WEI Peng-tao.Research on Boost Phase Spinning Error Correction by INS/GPS Combined Guidance Method[J].Modern Defence Technology,2012,40(1):85-89. |
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| Authors: | WEI Peng-tao |
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| Institution: | WEI Peng-tao(The Second Artillery Engineering University,Shaanxi Xi’an 710025,China) |
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| 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. |
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| Keywords: | spin flight in boost phase inertial navigation system/global position system(INS/GPS) Kalman filter hit accuracy |
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