基于滑模控制理论的前向追踪制导律研究  

Research on Head Pursuit Interception Guidance Law Based on Sliding Mode Control

作　　者：李之翰 王琦[1] 刘阳[1] 吴健健 Li Zhihan;Wang Qi;Liu Yang;Wu Jianjian(Nanehang Hangkong University,Nanehang 330063,China)

机构地区：[1]南昌航空大学,南昌330063

出　　处：《航天控制》2018年第6期25-30,35,共7页Aerospace Control

基　　金：航天科技创新基金项目资助(CAST2014CH01)

摘　　要：高超声速目标速度快,机动性高。使用传统拦截方式对目标进行拦截的难度过高,导致拦截精度下降。为了对高超声速目标拦截具有更高的制导精度,本文采用前向追踪拦截的方式对目标进行三维动态拦截仿真。根据目标与拦截器的运动学及动力学原理建立前向追踪拦截动态模型,该模型要求将低速拦截器置于高速目标之前;设计了一种基于滑模变结构控制理论前向追踪制导律,该制导律通过控制拦截器的法向加速度控制其飞行方向,从而达到拦截的目的;分析目标机动与非机动时拦截器的动态特性,并对目标在机动与非机动时与拦截器的运动轨迹及相关参数进行仿真,仿真结果验证了制导律的可行性。Hypersonic targets have higher speed and maneuverability.It is hard to intercept hypersonic targets by traditional interception mode which results in the decrease of intercept precision.In order to improve higher guidance precision of the hypersonic target interception,the head pursuit methods are used to simulate three -dimensional dynamic interception of the hypersonic target.Based on the principle of kinematics and dynamics,the dynamic model of head pursuit methods is established,and the low speed interceptor is placed before the high speed target in this model.A head pursuit interception guidance law is designed based on the sliding mode control theory,and the normal acceleration of the interceptor is controlled by the guidance law to change the flight direction regarding achieving the purpose of intercepting.The dynamic char- acteristics of interceptor are analyzed when target is maneuvering and non -maneuvering,and the trajectories and relevant parameters of target and interceptor are simulated when the target is maneuvering and non -maneuvering.The simulation results verify the feasibility of this proposed guidance law.

关 键 词：高超声速 前向追踪拦截 滑模控制 制导律 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]