高机动弹道目标末端拦截的新型有限时间滑模制导律设计  

A new finite-time sliding mode guidance law design in terminal interception of high maneuvering ballistic targets

作　　者：雷坤 梁勇奇[1] 蔡祥健 蔡光斌 LEI Kun;LIANG Yongqi;CAI Xiangjian;CAI Guangbin(State Key Laboratory for Strength and Vibration of Mechanical Structures,Xi’an Jiaotong University,Xi’an 710049,China;School of Missile Engineering,Rocket Force Engineering University,Xi'an 710025,China)

机构地区：[1]西安交通大学机械结构强度与振动国家重点实验室,陕西西安710049 [2]火箭军工程大学导弹工程学院,陕西西安710025

出　　处：《飞行力学》2020年第5期63-69,共7页Flight Dynamics

基　　金：国家自然科学基金资助(61773387);宇航动力学国家重点实验室开放基金资助(2015ADL-DW0203);中央高校基本科研业务费专项基金资助(xjj2016070);中国博士后科学基金资助(2017T100770,2016M590971)。

摘　　要：针对高机动弹道目标末端拦截问题,设计了一种具有有限时间收敛特性的新型滑模制导律。首先针对目标三维运动强耦合的特点,基于视线旋转坐标系内弹目相对运动关系建模,结合降维微分几何制导律和滑模控制理论,并采用快速双幂次趋近律构造了有限时间内快速收敛的连续制导指令;同时,采用了一种在末端拦截段使视线转率随弹目相对距离的减小在有限时间内快速收敛的滑模面;进而将目标的机动加速度视为上界未知的有界扰动,并通过自适应估计实现对目标加速度上界的快速逼近,可显著提高滑模面收敛速度,同时减弱抖震现象;最后,通过李雅普诺夫定律,对所提出新制导律的稳定性进行了证明。仿真结果表明,所设计的新型制导律能有效拦截高机动弹道目标。A new design method of sliding mode guidance law with finite-time convergence is presented for terminal interception of high maneuvering ballistic targets. Firstly, considering the strong coupling three-dimensional motion of the target, based on modeling of the relative motion of the missile and target in the rotating line of sight coordinate system, combining the dimension-reduction differential geometry guidance law with the sliding mode control theory, a fast double-power approaching law is utilized to construct a continuous guidance command with fast convergence in a finite-time. At the same time, a sliding surface which quickly converges infinite-time when the line of sight rate decreases with the relative distance of the missile and target at the terminal interception is adopted. Furthermore, the maneuvering acceleration of the target is regarded as the bounded disturbance with unknown upper bound, and adaptive estimator are applied to estimate the upper bound of the target’s acceleration, which could significantly improve the convergence rate of the sliding surface and reduce the chattering. The stability of the sliding mode guidance law is guaranteed by the Lyapunov stability theory. The simulation result results show that the design of the new guidance law can effectively intercept high maneuvering ballistic targets.

关 键 词：高机动弹道目标 滑模制导律 末端拦截 快速双幂次趋近律 加速度上界自适应估计 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]