小弹目速度比下拦截高超声速飞行器微分对策制导律研究  

Research on Differential Game Guidance Law for Intercepting Hypersonic Vehicles with Small Missile-to-Target Speed Ratio

作　　者：刘双喜 王一冲 朱梦杰 李勇 闫斌斌[3] LIU Shuangxi;WANG Yichong;ZHU Mengjie;LI Yong;YAN Binbin(Unmanned System Research Institute,Northwestern Polytechnical University,Xi’an 710072,Shaanxi,China;Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,Shaanxi,China)

机构地区：[1]西北工业大学无人系统技术研究院,陕西西安710072 [2]上海机电工程研究所,上海201109 [3]西北工业大学航天学院,陕西西安710072

出　　处：《空天防御》2022年第2期49-57,共9页Air & Space Defense

基　　金：航空基金(20200001053005);上海航天科技创新基金(SAST2020-004)。

摘　　要：针对高超声速飞行器拦截问题,利用非线性微分对策理论研究了小弹目速度比下高超声速飞行器拦截问题,将高超声速飞行器拦截问题转化为状态依赖参数(state-dependent coefficient,SDC)和代数黎卡提方程的求解,给出了基于状态依赖黎卡提方程方法微分对策制导律的解析形式。针对高超声速飞行器不机动、进行常值机动及不同弹目速度比的3种情况,分别进行仿真实验,并同比例导引律、自适应滑模制导律进行对比。实验结果表明,小弹目速度比下微分对策制导律可以有效地拦截高超声速飞行器。Aiming at the problem of intercepting hypersonic vehicles, the nonlinear differential game theory is applied to study the problem of intercepting hypersonic vehicles with small missile-to-target speed ratio. Thus, the interception problem is transformed into state-dependent coefficient(SDC) and algebraic Riccati Equation, and the analytical form of the differential game guidance law based on the state-dependent Riccati equation method is given. For the three scenarios of hypersonic vehicle with different maneuverability and different missile-to-target speed ratios, simulation experiments are carried out respectively. Meanwhile, comparisons are made with the proportional guidance law and the adaptive sliding mode guidance law, which demonstrates that the proposed guidance law can effectively intercept hypersonic vehicles with small missile-to-target speed ratio.

关 键 词：高超声速飞行器 微分对策 状态依赖黎卡提方程 小弹目速度比制导律 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]