基于碰撞航线的动能拦截器滑模制导律设计  

Sliding mode guidance law for KKV based on collision course

作　　者：杨旭[1] 张皎[1] 刘源翔[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《北京航空航天大学学报》2015年第11期2095-2102,共8页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家"863"计划(2011AA7043024);"985工程"三期重点建设项目

摘　　要：针对大气层外用于拦截目标动能拦截器(KKV)的制导律设计问题,采用非线性干扰观测器(NDO)及滑模变结构控制思想设计了一种基于碰撞航线的制导律.通过控制导弹攻角,使导弹的速度方向始终指向预期碰撞点,并利用NDO对目标加速度进行有效估计及动态补偿,降低了导弹所需的过载,并提高了命中时的速度.同时,分别从拦截轨迹、可拦截目标区域及拦截目标速度范围对机动目标进行拦截仿真,并与以零化视线角速率为目标设计的有限时间收敛制导律对比,仿真结果表明对于动能拦截器采用基于碰撞航线的滑模制导律具有更好的制导性能.Aimed at the problem of exoatmospheric kinetic kill vehicle（ KKV） guidance law design for intercepting targets,a novel missile sliding mode guidance law with nonlinear disturbance observer（ NDO）was derived base on collision course. Through steering angle of attack of missile,the direction of velocity of missile always pointed at the expected collision point. Missile could intercept the target with lower overload,faster speed via NDO,which was currently estimating and dynamically compensating to target acceleration.Moreover,comparison to the two interception strategies were obtained with interception trajectories,capture zones and velocity range. Another strategy was the sliding mode guidance law based on finite time convergence which aiming to steering the line of sight rate close to zero. The results show that the validities of the proposed sliding mode guidance law based on collision course in application for kinetic kill vehicle.

关 键 词：导弹制导 非线性干扰观测器 滑模控制 碰撞航线 拦截区域 

分 类 号：V488.13[航空宇航科学技术]