航空发动机分布式控制系统动态输出反馈鲁棒H_∞容错控制  

Dynamic output feedback robust H_∞ fault tolerant control for aero-engine distributed control system

作　　者：张乐迪 谢寿生[1] 张驭[1] 任立通[1] 王磊[1] 彭靖波[1] 周彬[1] ZHANG Ledi;XIE Shousheng;ZHANG Yu;REN Litong;WANG Lei;PENG Jingbo;ZHOU Bin(Aeronautics and Astronautics Engineering College,Air Force Engineering University,Xi＇an 710038,China)

机构地区：[1]空军工程大学航空航天工程学院,西安710038

出　　处：《航空动力学报》2018年第6期1519-1527,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51476187;51506221;51606219);陕西省自然科学基础研究计划(2015JQ5179)

摘　　要：针对存在网络诱导时延、外部干扰的航空发动机分布式控制系统,提出了执行机构发生部分失效故障时的输出反馈容错控制方法。对航空发动机分布式控制系统中网络诱导时延以及执行器部分失效问题进行量化说明,在此基础上,采用动态输出反馈控制器建立增广闭环系统。针对所建立的增广闭环系统,对H_∞性能约束下的增广闭环系统稳定性进行分析,并利用线性矩阵不等式理论设计了输出反馈H_∞容错控制器。仿真结果表明,当两个执行机构输出值分别为衰减80%和50%时,控制系统在所设计的控制器作用下均方渐进稳定,且具有H_∞性能指标为0.63,同样在正向偏差故障条件下也具有很好的容错能力。The output feedback fault tolerant control strategy was proposed for aero-engine distributed control system with network induced time delay and disturbance in occurrence of actuator partial fault.The areo-engine distributed control system model parameters were described quantitatively,and the closed-loop system was established based on dynamic output feedback controller.The stability analysis under the constraint of H∞ performance was given for the augmented closed-loop system,based on which the design approach of output feedback H∞fault-tolerant controller was designed by means of linear matrix inequality.Simulation results showed that the system was asymptotically stable with the devised controller when actuator attenuation faults were 80% and 50%,respectively,and had a certain H∞ performance index 0.63.Similarly,then system had a good fault tolerant performance when actuator attenuation faults occurred.

关 键 词：分布式控制系统 动态输出反馈 执行器部分失效故障 网络诱导时延 鲁棒H∞容错控制 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]