基于LMI涡扇发动机混合加权灵敏度H_∞动态输出反馈控制  

Turbo-Fan Engine Dynamic Output Feedback Control with Mixed Weighted Sensitivity Based on LMI

作　　者：覃道亮[1] 王曦[1] 郑铁军[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》2005年第2期309-313,共5页Journal of Aerospace Power

摘　　要：利用回路整形和内模原理方法,选取合理频率域加权函数,结合实际被控对象状态空间模型,得到某广义被控对象状态空间模型,将原控制要求问题转化为标准H∞控制问题。基于LMI(LinearMatrixInequality)方法,对此广义对象进行最优H∞动态输出反馈控制器设计,进而求得原被控对象的控制器。以某型涡扇发动机为被控对象,进行混合加权灵敏度H∞动态输出反馈控制器设计,并在飞行包线范围内,进行了发动机控制系统非线性仿真验证。结果表明,此控制器满足抗干扰性、跟踪性要求,并具有一定鲁棒性。Choosing appropriate weighted functions in the frequency domain, and in combination with the state-space model of the real plant, the formulation of the state-space model for some generalized plant by employing the method of loop shaping and internal principle was established. The original control problem was converted to a standard H∞ problem. The controller for the original plant was derived by means of solving optimal H∞ dynamic output feedback controller for the generalized plant based on Linear Matrix Inequality (LMI). This design procedure was applied to a turbo-fan engine. The controller obtained by this method was verified in a wide engine operating range in the flight envelope. Simulation results of the turbofan engine nonlinear model show that the characteristics of the controller, namely, tracking characteristics, disturbance rejection and robustness, are satisfactory.

关 键 词：航空、航天推进系统 回路整形 内模原理 LMI H∞ 动态输出反馈 

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]