高超声速飞行器舵面故障Nussbaum增益自适应容错控制  

Nussbaum Gain Adaptive Fault Tolerant Control for Hypersonic Vehicle with Elevator Faults

作　　者：徐斌彦 齐瑞云[1] 姚雪莲[2] 

机构地区：[1]南京航空航天大学自动化学院,南京210016 [2]江苏理工学院汽车与交通工程学院,常州213001

出　　处：《战术导弹技术》2017年第4期103-112,共10页Tactical Missile Technology

基　　金：国家自然科学基金(61374116);江苏省"六大人才高峰"高层次人才项目(HKHT-010)

摘　　要：针对双舵面的高超声速飞行器的纵向模型,并且考虑到舵面故障和系统参数不确定的问题,设计自适应容错跟踪控制器。首先,对于高度子系统,由于系统中存在不确定量,对其参数化并设计自适应估计律,再通过反馈线性化设计理想控制信号。其次,考虑到舵面故障,根据推导得到的容错参数与故障参数的匹配条件,得到对容错参数的约束条件,并且运用Nussbaum增益函数自适应估计由舵面故障引起的不确定控制方向。自适应容错高度跟踪控制律设计完成后,运用Lyapunov稳定性理论验证了整个闭环控制系统的稳定性。同样的控制方案也可被应用在速度跟踪控制器的设计上。最后,仿真结果进一步说明控制器设计的合理有效性。An adaptive fault tolerant controller is designed for the longitudinal motion of a twin-elevator hypersonic vehicle containing uncertain parameters and unexpected elevator faults. Firstly,for altitude subsystem,parameterization and adaptive laws are applied,and feedback linearization is used to design a desired control signal. Then,in consideration of elevator faults,the appropriate range of the fault tolerant parameters is chosen on the account of the obtained matching conditions between the fault tolerant parameters and fault parameters. Nussbaum gain adaptive control method is adopted to handle the unknown control direction problem resulted from elevator faults. An adaptive fault tolerant altitude control law is developed,and the asymptotic stability of the closed-loop system output is proved through Lyapunov standard theory. The same method of control is also applied to develop the tracking controller. Finally,a simulation example is carried out to evaluate the effectiveness.

关 键 词：高超声速飞行器 容错控制 Nussbaum增益自适应控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]