鲁棒控制用于涡喷发动机控制器设计  

Application of Robust Control to the Design of Jet Engine Digital Controller

作　　者：王曦[1] 杨杰[1] 覃道亮[1] 田凤欣[2] 王海龙[2] 

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 [2]北京长空机械有限责任公司,北京100101

出　　处：《航空动力学报》2005年第4期679-683,共5页Journal of Aerospace Power

摘　　要：基于LMI(LinearMatrixInequality,线性矩阵不等式)的方法,将PID控制律与鲁棒技术交叉结合,考虑了控制受限条件,提出了一种基于LMI的输出反馈PI控制器分段设计的切换方法。这一技术应用于某型涡喷发动机全功能的数字式电子控制器的稳态控制中,并介绍了该型涡喷发动机控制系统的组成,包括硬件、软件、步进电机执行机构及燃油计量装置。设计的电子控制器在发动机半实物仿真平台上进行了鲁棒性能的验证,实现了电子控制器的等转速调节功能和逻辑监控保护功能,满足涡喷发动机多功能FADEC控制要求。Based on the LMI （Linear Matrix Inequality） method ,the PID （Proportional Integral Derivative） control law was combined with robust control technique, and the subsection switch skill of PI output feedback control design with constraint of control input for aero-engine was proposed. The technology was applied to the steady state control of the full function digital electronic control system of a jet engine. The constitution of the system,including hardware, software,step motor actuating mechanism and fuel metering device,was introduced. Electronic controller not only can control the rotating speed stable but also have enough logic,multiple control monitor and protective functions. It fulfills allsigned electronic controller has been carried hardware-in-loop simulation platform.requirements of multiple FADEC control. The dethrough robust validity check on the engine semihardware-in-loop simulation platform.

关 键 词：航空 航天推进系统 数字式电子控制器 PI控制 鲁棒性能 LMI方法 半实物仿真 涡喷发动机 

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]