飞机作动器的故障辨识与自修复控制  

Actuator fault identification and reconfigurable control for aircraft

作　　者：王永[1] 郭志伟[1] 彭程[1] 

机构地区：[1]中国科学技术大学自动化系,合肥230027

出　　处：《东南大学学报（自然科学版）》2010年第S1期1-7,共7页Journal of Southeast University：Natural Science Edition

摘　　要：为了解决作动器发生故障的飞机的角速率跟踪问题,提出了一种基本控制律加修复控制向量的自修复控制方案.该方案首先针对飞机的无故障模型,利用反步法设计角速率跟踪控制律作为基本控制律.在作动器发生故障的情况下,保持基本控制律不变,将飞机作动器视为二阶系统,设计了一种基于高增益观测器的作动器故障参数估计器,对作动器的各类故障进行辨识;根据故障辨识结果构造修复控制向量以抵消作动器故障产生的影响,保证故障后系统的跟踪性能.对某型飞机发生右副翼卡死故障进行仿真,结果表明,故障参数的估计值能够快速收敛到真值,构造的修复控制向量能够将系统性能恢复到无故障时的水平,验证了所提出的自修复控制方案的有效性.An algorithm for angular rate tracking of the aircraft with actuator fault is presented, which consists of basic control law and reconfigurable control vector. A basic control law is designed using backstepping technology for the fault-free aircraft. When actuator faults occur,the basic control law is maintained. Taking into account the dynamic characteristic of second-order for the aircraft actuator,an on-line fault parameter estimator is designed based on high-gain observer,which can identify various types of actuator faults. A reconfigurable control vector is implemented by using the estimated fault parameters,which compensates the influence of actuator fault and guarantees the tracking performance of the aircraft with actuator fault. The simulation of an aircraft with the stuck of right aileron was performed. Results show that the estimated values can rapidly converge to the corresponding true values and the reconfigurable control vector can restore the tracking performance to the level of the fault-free system. Therefore the effectiveness of the proposed algorithm is verified.

关 键 词：自修复控制 高增益观测器 故障辨识 反步法 作动器故障 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计] V267