非最小相位高超声速飞行器自适应鲁棒容错控制  

Robust adaptive fault tolerant control for non-minimum phase hypersonic vehicle

作　　者：魏启钊 齐瑞云[1,2] 姜斌[1,2] WEI Qizhao;QI Ruiyun;JIANG Bin(College of Automation Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Key Laboratory of Navigation,Control and Health-Management Technologies of Advanced Aerocraft,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China)

机构地区：[1]南京航空航天大学自动化学院,江苏南京211106 [2]南京航空航天大学先进飞行器导航、控制与健康管理工业和信息化部重点实验室,江苏南京211106

出　　处：《西北工业大学学报》2021年第S01期1-9,共9页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(61873127,62020106003)资助。

摘　　要：针对具有非最小相位特性的高超声速飞行器纵向动力学模型,考虑舵面发生卡死和失效故障、系统参数不确定的问题,提出了一种基于输出重定义形式的自适应鲁棒容错控制方法。对于高度子系统中由于升降舵和升力耦合产生的不稳定内动态,重定义系统输出,将俯仰角作为系统新的输出,对新内动态进行一些坐标变换,设计出俯仰角期望的跟踪指令。对于系统重定义后的高度和速度子系统,将未知非线性函数参数化并写成未知气动参数和函数向量的乘积形式,采用自适应学习律估计未知气动参数和故障参数,基于Lyapunov稳定性定理进行了系统稳定性理论分析,通过仿真验证了所给方法的有效性。A robust adaptive fault-tolerant controller based on output redefinition is proposed for non-minimum phase Hypersonic vehicle models with parametric uncertainties and elevator faults.First,for the unstable internal dynamics caused by the coupling of elevator and lift in the altitude subsystem,the system output is redefined,the pitch angle is taken as the new output of the system,some coordinate transformations are performed on the new internal dynamics,and the desired tracking command for the pitch angle is designed.For the redefined altitude and velocity subsystem of the system,the unknown nonlinear function is parameterized and written as the product of unknown aerodynamic parameters and function vectors,and the adaptive law is used to estimate the unknown aerodynamic parameters and failure value.Finally,the stability of the system is analyzed via the Lyapunov approach.The effectiveness of the proposed method is verified by the simulation results.

关 键 词：非最小相位 高超声速飞行器 自适应控制 容错控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]