航空发动机H_∞/PI输出反馈控制——非严格正则LMI方法  

H_∞/PI Output Feedback Control of Aero-Engine Under Nonstrict Properness Based on LMI

作　　者：王曦[1] 覃道亮[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《航空动力学报》2004年第2期254-258,共5页Journal of Aerospace Power

摘　　要：基于传递函数矩阵H∞范数的等价原则思想,将非严格正则模型转化为严格正则模型。通过LMI求解方法,在考虑控制能量约束的条件下,对严格正则模型进行静态输出反馈PI控制器设计。提出了一种非严格正则模型静态输出反馈PI控制器求解的算法。以某型双转子涡喷发动机为被控对象,进行静态输出反馈PI控制器的LMI设计,并分区域在飞行包线进行了动静态性能和鲁棒性能仿真验证。According to the physical meaning of the H∞ norm, a nonstrict proper model was converted into some strict proper model under the equivalence condition of their H∞ norms. A static output feedback PI controller for the resulting strict proper model was designed on the basis of LMI, and control constraints were taken into consideration in the design process of the controller. An algorithm for solving the static output feedback PI controller was presented. This method was applied to the design procedure of aero-engine controller. The dynamical and static performances of the aero-engine control system were verified at different partitioned regions of flight envelope.

关 键 词：传递函数矩阵H∞范数 航空发动机 输出反馈控制 非严格正则模型 LMI设计 

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]