对临近空间飞行器的多弹协同拦截策略研究  

Research on Cooperative Multiple-missile Intercepting Strategy for Near-space Vehicles

作　　者：惠耀洛 南英[1] 陈哨东 杨毅[1] 

机构地区：[1]南京航空航天大学航天学院,南京210016 [2]国家光电重点实验室,河南洛阳471009

出　　处：《弹箭与制导学报》2015年第5期149-154,共6页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：南京航空航天大学研究生创新基地(实验室)开放基金(kfjj201458);中央高校基本科研业务费专项资金资助

摘　　要：为实现对临近空间高超声速飞行器的有效拦截,文中提出了多对多饱和拦截策略。首先采用实时在线的遗传算法寻优,对拦截武器系统进行动态任务分配。其次,基于滑模变结构控制理论,设计了4-D(三维几何空间与时间)协同制导律,控制拦截的弹着时间基本相同,在拦截末段,采用纯比例制导律,控制拦截弹对目标实施高精确协同打击。仿真结果表明,该拦截策略可以对临近空间高超声速飞行器目标进行高可靠度拦截和高精确度打击。This paper provides an effective intercepting strategy for mission intercepting near-space vehicles using multi-to-multi confrontation. Concrete research was constitutive of the following two parts： firstly,intercepting tasks were allocated to flight vehicles based on genetic algorithm to optimize efficiency of intercepting system. Secondly,the 4-D impact time control guidance law（ ITCG） was designed in forepart of interception based on theory of sliding mode control for basically identical intercepting time. Pure PNG law was adopted in terminal maneuvering ballistic trajectory to ensure that cooperative interception was accurate. Numerical simulation results show that this intercepting strategy can achieve highly reliable and accurate interception for multiple missiles intercepting multiple hypersonic near-space vehicles.

关 键 词：动态任务分配 时间协同制导律 遗传算法 滑模变结构控制理论 临近空间飞行器 飞行仿真 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]