考虑驾驶仪动态特性的非奇异快速终端滑模导引律  

Nonsingular Fast Terminal Sliding Mode Guidance Law Considering the Dynamic Characteristics of Autopilot

作　　者：张宽桥 杨锁昌 傅振华 刘畅 Zhang Kuanqiao;Yang Suochang;Fu Zhenhua;Liu Chang(Department of Missile Engineering,Shijiazhuang Campus of Army Engineering University,Shijiazhuang 050003,China;School of Automation,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]陆军工程大学石家庄校区导弹工程系,石家庄050003 [2]北京理工大学自动化学院,北京100081

出　　处：《战术导弹技术》2019年第6期74-81,共8页Tactical Missile Technology

摘　　要：针对某些导弹在打击目标时需要满足攻击角度约束要求,基于终端滑模控制、有限时间收敛稳定性理论和动态面控制,设计了一种考虑自动驾驶仪动态特性的导引律。首先,设计了一种非奇异快速终端滑模面,结合自适应指数趋近律,推导出一种带攻击角度约束的自适应非奇异快速终端滑模导引律。该导引律克服了传统终端滑模导引律存在的奇异问题,实现了制导系统状态的全局有限时间收敛,缩短了收敛时间。然后,采用动态面控制改进该导引律,提出了一种考虑自动驾驶仪动态特性的导引律,并通过仿真试验验证了所设计导引律的有效性和优越性。Based on the theories of terminal sliding mode control,finite time convergence stability and dynamic surface control,a guided law considering the dynamic characteristics of missile autopilot is designed for some missiles to meet the requirement of angle constraint.Firstly,an adaptive fast nonsingular terminal sliding mode guidance law with impact angle constraint is improved by designing an nonsingular fast terminal sliding mode surface and combining it with an adaptive exponential reaching law.The guidance law can overcome the singularity problem of the traditional terminal sliding mode guidance law and improve the global finite time convergence of the guidance system states to shorten the convergent time.Then,based on the dynamic surface control method,a guidance law constraint considering the dynamic characteristics of the autopilot is proposed.Simulation experiments verify the effectiveness and superiority of the law.

关 键 词：导引律 非奇异终端滑模控制 动态面控制 攻击角度约束 指数趋近律 自动驾驶仪 导 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]