| 弹道导弹助推段拦截最优制导律设计 |
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| 引用本文： | 崔彦凯,梁晓庚,王斐,胡艳娜.弹道导弹助推段拦截最优制导律设计[J].飞行力学,2011,29(1):59-62. |
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| 作者姓名： | 崔彦凯 梁晓庚 王斐 胡艳娜 |
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| 作者单位： | 西北工业大学自动化学院;空空导弹研究院科技部;中国人民解放军第五七一五工厂第七车间; |
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| 摘 要： | 针对弹道导弹助推段飞行中加速度大、飞行速度高、拦截反应时间短的特点,研究最优拦截直接碰撞制导律.在建立拦截弹与目标相对运动方程的基础上,以终端脱靶量最小和能量最省为性能指标,设计了空射反导导弹在助推段拦截弹道导弹目标的最优制导律.仿真结果表明,所设计的制导律满足设计指标,达到了直接碰撞杀伤目标的目的,验证了所设计制导律...
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| 关 键 词： | 弹道导弹 助推段拦截 直接碰撞 最优制导律 |
Design of optimal guidance law for interception ballistic missile during the boost phase |
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| CUI Yan-kai,LIANG Xiao-geng,WANG-Fei,HU Yan-na.Design of optimal guidance law for interception ballistic missile during the boost phase[J].Flight Dynamics,2011,29(1):59-62. |
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| Authors: | CUI Yan-kai LIANG Xiao-geng WANG-Fei HU Yan-na |
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| Institution: | CUI Yan-kai1,LIANG Xiao-geng1,2,WANG-Fei1,HU Yan-na3(1.College of Automation,Northwestern Polytechnical University,Xi'an 710072,China,2.Department of Technology,China Airborne Missile Academy,Luoyang 471009,3.Seventh Workshop,5715th Factory of the PLA,China) |
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| Abstract: | This paper studied a direct hit optimal guidance law of interception,aiming at the characteristics of acceleration high,flight velocity rapid and reaction time short for ballistic missile during the boost phase.Relative motion equations of interception missile and ballistic missile were founded;the performance index function was designed to reach undershoot quantity least and energy minimum.The optimal guidance law of defense missile launched by airplane was designed for interception ballistic missile durin... |
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| Keywords: | ballistic missile boost phase intercept direct hit optimal guidance law |
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