高超声速飞行器自适应固定时间抗饱和控制  

Fixed-time antisaturation adaptive control of a hypersonic vehicle

作　　者：刘继承 江驹[1] 阴浩博 刘亮 LIU Jicheng;JIANG Ju;YIN Haobo;LIU Liang(College of Automatic Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学自动化学院,江苏南京210016

出　　处：《哈尔滨工程大学学报》2022年第7期1013-1022,共10页Journal of Harbin Engineering University

基　　金：国家自然科学基金项目(61673209,71971115);南京航空航天大学研究生创新基地(实验室)开放基金项目(kfjj20200333)。

摘　　要：针对参数不确定和外界干扰下的高超声速飞行器的控制问题,本文提出了一种自适应固定时间控制方法。采用反馈线性化方法对高超声速纵向动力学模型进行输入输出线性化,并基于固定时间控制理论针对该线性模型分别设计了速度和高度通道的固定时间自适应高阶滑模控制器,提高了系统的收敛速度。对于执行器饱和问题,设计了一种新型抗饱和辅助系统并引入控制器中。基于李雅普诺夫理论对所设计的控制器进行严格证明,得到了闭环系统的固定时间收敛特性。与现有文献高阶滑模控制方法进行仿真对比实验,验证了本文所设计方法的有效性和鲁棒性。A novel adaptive fixed-time control scheme is presented to control hypersonic vehicles under parameter uncertainty and external disturbance.The feedback linearization method achieved output/input linearization for the typically longitudinal dynamic model on a hypersonic flying vehicle.Based on the fixed-time control theory,the fixed-time adaptive high-order sliding mode controllers for speed and altitude sub-systems are designed for this linear model,which improves the convergence speed of the system.A novel antisaturation auxiliary system is designed and introduced to the controller to solve the saturation problem of the actuator.The designed controller is strictly proved using Lyapunov theory,yielding the closed-loop system′s fixed-time convergence characteristic.Finally,a simulation experiment comparing the proposed method to the high-order sliding mode control method in the existing literature validates its effectiveness and robustness.

关 键 词：高超声速飞行器 参数不确定 外界干扰 非线性控制 固定时间控制 高阶滑模 自适应控制 输入受限 鲁棒控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]