基于滑模方法与跟踪微分器的时间约束制导律  

Time-constraint guidance law based on sliding mode method and tracking differentiator

作　　者：王永骥[1,2] 安炳合 刘磊 王博[1,2] WANG Yongji;AN Binghe;LIU Lei;WANG Bo(School of Artificial Intelligence and Automation,Huazhong University of Science and Technology,Wuhan 430074,China;National Key Laboratory of Science and Technology on Multispectral Information Processing,Huazhong University of Science and Technology,Wuhan 430074,China)

机构地区：[1]华中科技大学人工智能与自动化学院,湖北武汉430074 [2]华中科技大学多谱信息处理技术国家重点实验室,湖北武汉430074

出　　处：《华中科技大学学报（自然科学版）》2020年第10期1-6,共6页Journal of Huazhong University of Science and Technology(Natural Science Edition)

基　　金：国家自然科学基金资助项目(61873319,61903146,61803162)。

摘　　要：针对具有攻击时间约束的导弹末制导问题,设计了一种基于滑模方法与新型跟踪微分器的制导律.首先,给出了导弹-目标相对运动模型,在此基础上根据已飞行时间加剩余飞行时间等于期望攻击时间的思想选取滑模变量,滑模变量收敛后,可以满足攻击时间约束;然后,设计滑模制导律保证滑模变量的收敛性,并对制导律的奇异性进行了分析;为了获得视线角速率,提出了一种基于反双曲正弦函数的新型跟踪微分器;最后,在数值仿真中使用该制导律对导弹进行控制.仿真结果证明该制导律能够使制导过程满足攻击时间的要求.Aiming at solving the terminal guidance problem with attack time constraint,a guidance law based on the sliding mode method and new tracking differentiator was designed.Firstly,the missile-target relative motion model was introduced.The sliding mode variable was chosen based on the idea that the sum of the already flight time and the remaining flight time was equal to the expected flight time.When the sliding mode variable converged to the origin,the attack time constraint could be satisfied.Then,the sliding mode guidance law was designed to ensure the convergence of the sliding mode variable,and the singularity of the guidance law was analyzed.To obtain the line of sight rate,a new tracking differentiator based on inverse hyperbolic sine function was proposed.Finally,the missiles were controlled by the proposed sliding mode guidance law for numerical simula-tions.Simulations results show that the guidance process can meet the requirements of attack time by using the proposed guidance law.

关 键 词：制导律 攻击时间约束 剩余飞行时间 滑模方法 新型跟踪微分器 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]