航空发动机准滑动模态变结构控制  

Application of Quasi-Variable Structure Control Method in Aeroengine Control System

作　　者：章仁华[1] 马静[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《计算机仿真》2011年第1期103-106,118,共5页Computer Simulation

摘　　要：针对航空发动机不确定因素多的特点,主要由各种干扰和机械振动引起动特性恶化。为解决上述问题,将幂次趋近律的准滑动模态变结构控制方法应用于航空发动机控制系统。滑模变结构控制方法具有参数摄动和干扰等不确定因素"不变性"的特点,采用准滑模控制系统可以有效地避免或削弱一般滑模控制系统中的抖振问题,采用幂次趋近律以提高发动机控制系统在趋近运动阶段的动态品质,并对飞行包线内不同点的控制系统进行了仿真,仿真结果表明,趋近律准滑态变结构所设计的发动机控制系统有效提高了系统的鲁棒性和抗干扰能力,并消除了系统的抖动。The quasi-sliding mode variable structure control method with power reaching law is proposed and used in an aeroengine control systems which has much uncertainty factors. The sliding model variable structure control method has the features of the invariance of uncertain factors such as parameter perturbation and jamming. The quasi -sliding mode control system is a good solution to avoid or weaken the problem that the buffeting appears in the general sliding mode control system. The quality of engine control system in dynamic movement is improved by using the power reaching law, and the control system of different points in the flight envelope is simulated. It can be drawn from the simulation that, designed with the quasi-slide mode variable structure based on reaching law, the engine control system has good control performance.

关 键 词：航空发动机 趋近律准滑态变结构 多变量解耦控制 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计]