| 寻的导弹寄生天线罩耦合回路有效导航比设计 |
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| 引用本文： | 林世雄.寻的导弹寄生天线罩耦合回路有效导航比设计[J].上海航天,2007,24(4):7-12. |
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| 作者姓名： | 林世雄 |
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| 作者单位： | 上海机电工程研究所,上海,200233 |
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| 摘 要： | 基于比例导引(PN)制导律和实际惯性稳定框架式导引头回路,针对导引头回路两种校正网络,建立了用于设计有效导航比的两种寻的导弹寄生天线罩耦合回路模型,给出了PN寻的制导系统的控制弹道实际有效导航比的计算公式及设计准则。算例结果表明,该方法正确有效,所得脱靶量较小。
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| 关 键 词： | 寻的导弹 比例导引 导引头回路 寄生天线罩耦合回路 有效导航比 寻的制导 |
| 文章编号： | 1006-1630（2007）04-0007-06 |
| 收稿时间： | 2006-05-24 |
| 修稿时间： | 2006-12-07 |
Design of Effective Navigation Ratio for Parastitic Radome Coupling Loop in Homing Missile |
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| LIN Shi-xiong.Design of Effective Navigation Ratio for Parastitic Radome Coupling Loop in Homing Missile[J].Aerospace Shanghai,2007,24(4):7-12. |
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| Authors: | LIN Shi-xiong |
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| Abstract: | Based on proportional navigation(PN) guidance law and real radar seeker head loop for inertial stability gimbal,the two models of the parasitic radome coupling loop for PN homing guidance law to design effective navigation ratio in terms of two types of demenselop network for the seeker loop was put forward in this paper.The computation equation and design criterion of real effective navigation ratio of homing control trajectory in PN homing guidance system were given.The calculation results showed that this method was effective,which could acquire small miss distance. |
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| Keywords: | Homing missile Proportional navigation guidance law Seeker loop Parasitic radome coupling loop Effective navigation ratio Homing guidance |
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