基于零脱靶量设计的前向追踪拦截滑模制导律  

Head Pursuit Interception Sliding Mode Guidance Law Based on Zero Miss-distance

作　　者：贾杰[1] 李永强[1] 陈晨[1] 周艳艳[1] 

机构地区：[1]南昌航空大学,南昌330063

出　　处：《航天控制》2013年第1期27-31,共5页Aerospace Control

基　　金：国家自然科学基金(61263012);中国博士后科学基金(2012M510593)

摘　　要：在拦截高超音速目标时,传统拦截制导律要求拦截弹速度更高,由此带来拦截弹的能量和控制等诸多难题。本文设计了一种基于零脱靶量的前向追踪拦截滑模制导律,实现了低速拦截弹拦截高速目标。首先分析了前向追踪拦截模型,该模型将低速拦截弹放置在高速目标前方飞行,通过控制拦截弹的飞行方向,可以达到拦截目标的目的;然后给出了前向追踪模型下理论脱靶量在目标机动和非机动两种情况下的数学表达式;最后以目标机动情况下的理论脱靶量为滑模面,设计了一种基于滑模控制的前向追踪拦截制导律。仿真试验验证了该制导律的可行性和高精度、低过载的特点。The higher speed is required for interceptor in the traditional interception guidance law during intercepting hypersonic targets. It results in a lot of difficult problems such as the energy and control of interceptor. Based on zero miss-distance, a head pursuit interception sliding mode control guidance law is designed, which allows the low-speed interceptor to intercept the high-speed target. Firstly, the model of head pursuit interception that the low-speed interceptor flies towards the front of the high-speed target is analyzed. By controlling the flight direction, the target can be intercepted. Then, the math expressions of miss-distance which in the both cases of maneuvering target and nonmaneuvering target are presented. Finally, the miss-distance which in the case of maneuvering target is considered as the sliding surface and the head pursuit interception guidance law based on sliding control is proposed. The simulation shows that this feasibility, high accuracy and low overload of this proposed guidance law.

关 键 词：前向追踪 拦截 滑模控制 制导律 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]