小速度比视角下高超声速飞行器拦截条件研究  

Research on Hypersonic Vehicle Interception Conditions from a Small Velocity Ratio Perspective

作　　者：刘双喜 闫斌斌[2] 张通[1] 张旭[1] 闫杰[1,3] Liu Shuangxi;Yan Binbin;Zhang Tong;Zhang Xu;Yan Jie(Unmanned System Research Institute,Northwestern Polytechnical University,Xi’an 710072,China;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;Research Center for Unmanned System Strategy Development,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学无人系统技术研究院,西安710072 [2]西北工业大学航天学院,西安710072 [3]西北工业大学无人系统发展战略研究中心,西安710072

出　　处：《航空兵器》2023年第3期67-73,共7页Aero Weaponry

基　　金：航空科学基金项目(20200001053005);上海航天科技创新基金项目(SAST2020-004)。

摘　　要：针对高超声速飞行器拦截问题,以吸气式高超声速飞行器为拦截对象,从拦截态势出发,利用交战几何概念,基于小速度比(拦截弹的速度小于高超声速飞行器的速度)视角,理论上给出了成功拦截高超声速飞行器的必要条件以及高超声速飞行器速度前置角的约束条件。然后,以真比例导引律为例,针对高超声速飞行器不同机动模式,给出了拦截弹拦截空间的数学表达式。最后,通过仿真实验,给出了不同速度比、高超声速飞行器不同机动模式下,拦截弹拦截空间的变化曲线,系统性地分析小速度比视角下拦截高超声速飞行器的拦截条件,为后续拦截高超声速飞行器中末制导交接班条件和末制导律设计提供基础理论依据。To address the problem of hypersonic vehicle interception,taking the air-breathing hypersonic vehicle as the target of interception,this paper employs the concept of engagement geometry to theoretically provide the necessary conditions for the successful interception of hypersonic vehicles as well as constraints on the velocity-leading angle of hypersonic vehicle from the perspective of a small velocity ratio(the velocity of the interceptor is lower than that of the hypersonic vehicle)based on the interception posture.Then,it puts forward the mathematical expressions for the interception space of the interceptor for different maneuvering modes of the hypersonic vehicle,taking the true proportional guidance law as an example.Finally,by simulation experiments,it presents the interception space changing curves on the conditions of different velocity ratios and different maneuvering modes of hypersonic vehicles,and systematically analyses the conditions of intercepting hypersonic vehicles from a small velocity ratio perspective.This study can provide a fundamental theoretical basis for the mid-end guidance handover conditions and guidance law design for the subsequent interception of hypersonic vehicles.

关 键 词：交战几何 小速度比 拦截空间 比例导引律 高超声速飞行器 

分 类 号：TJ760[兵器科学与技术—武器系统与运用工程] V249[航空宇航科学与技术—飞行器设计]