高超声速飞行器积分滑模自抗扰控制研究  

Research on Integral Sliding Mode Active Disturbance Rejection Control for Hypersonic Vehicles

作　　者：唐伟强[1] 甲成超 石文科 许天鹏[1] TANG Weiqiang;JIA Chengchao;SHI Wenke;XU Tianpeng(College of Electrical and Information Engineering,Lanzhou University of Technology,Lanzhou 730050,China)

机构地区：[1]兰州理工大学电气工程与信息工程学院,甘肃兰州730050

出　　处：《现代防御技术》2024年第5期40-50,共11页Modern Defence Technology

基　　金：国家自然科学基金(62063018);甘肃省科技计划(22JR5RA225,23CXGA0002)。

摘　　要：针对高超声速飞行器不确定性问题,提出了一种自抗扰控制与积分滑模控制结合的跟踪策略。通过对高超声速飞行器模型的分析,将其转变为速度子系统和高度子系统,其中速度子系统是典型的一阶系统,高度子系统则由高度环、航迹角环、俯仰角环组成。采用跟踪微分器安排系统的过渡过程,使用扩张状态观测器对系统总扰动进行估计。设计积分滑模控制律代替自抗扰控制中的非线性状态误差反馈控制律。结果表明所设计的跟踪控制策略对不确定性具有很强的鲁棒性,与传统滑模自抗扰控制相比,其在调节时间、跟踪精度和控制信号平滑性方面更有优势。Aiming at the uncertainty problem of hypersonic vehicles,a tracking strategy combining active disturbance rejection control and integral sliding mode control is proposed.The hypersonic vehicle model is transformed into a velocity subsystem and an altitude subsystem,where the velocity subsystem is a first-order system,and the altitude subsystem consists of the altitude loop,track angle loop,and pitch angle loop.Tracking differentiator is used to arrange the transition process of the system,and extended state observer is used to estimate the total disturbance.The integral sliding mode control law is designed to replace the nonlinear state error feedback control law.The results show that the designed tracking control strategy has strong robustness to hypersonic vehicle uncertainty.Compared with the traditional sliding mode active disturbance rejection control,it has more advantages in adjustment time,tracking accuracy and control signal smoothness.

关 键 词：高超声速飞行器 不确定性问题 自抗扰控制 积分滑模控制 鲁棒性 

分 类 号：V448[航空宇航科学与技术—飞行器设计] TJ8[兵器科学与技术—武器系统与运用工程]