基于Terminal滑模的动能拦截器末制导律研究  

Terminal Guidance Law of Kinetic Interceptor Based on Terminal Sliding Mode

作　　者：汤一华[1] 陈士橹[1] 徐敏[1] 万自明[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《空军工程大学学报（自然科学版）》2007年第2期22-25,共4页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航天支撑技术基金资助项目(XG01)

摘　　要：针对大气层外动能拦截器的精确拦截问题,给出了一种基于Terminal滑模的鲁棒末制导律设计方法。在不考虑动能拦截器姿态运动的情况下,建立了动能拦截器纵向平面和侧向平面内的相对运动方程,并通过在末制导滑模中引入非线性项,去除了传统变结构制导律中的切换项,保证制导系统具有全局快速性。仿真结果表明Terminal滑模应用于动能拦截器精确末制导律设计中的有效性,较之传统的比例导引和变结构制导方法,能有效抑制视线的发散,对目标机动具有更强的鲁棒性,并具有更高的拦截精度。A terminal guidance law based on the terminal sliding mode technology is proposed for the precise interception of exo - atmospheric kinetic interceptor. Firstly, the longitudinal and lateral equations of relative motion are built without considering the kinetic interceptor＇s attitude motion. Then the nonlinear terms are introduced into the mode designing of terminal guidance law, so this terminal guidance law doesnt have the switch terms that exist in the traditional variable structure guidance law and can ensure the global speediness of guidance system. The simulation results show that the method used in the terminal guidance of kinetic interceptor is effective and it＇s better than the proportional navigation and traditional variable structure guidance law in robustness and precision when intercepting the maneuvering targets.

关 键 词：动能拦截器 末制导 TERMINAL滑模 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]