基于广义GB引理的航空发动机准滑模控制  

Quasi - Sliding Mode Control of Aeroengine Based on Generalized GB Lemma

作　　者：曹惠玲[1] 郑里鹫 李玉铭 CAO Hui-ling;ZHENG Li-jiu;LI Yu-ming(College of Aeronautical Engineering,CAUC,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300

出　　处：《计算机仿真》2020年第12期20-24,262,共6页Computer Simulation

基　　金：中国民航大学博士启动基金(项目编号QD02s04)。

摘　　要：以一类航空发动机非线性模型为研究对象,在传统的滑模控制基础上引入补偿算法设计转速调节控制律。利用广义Gronwall-Bellman引理对闭环系统的稳定性进行分析,并给出在一定初值条件下状态变量二范数的边界约束关系,可通过对控制律参数的选取对状态变量范数边界进行调节,使得系统渐进稳定于平衡状态。利用MATLAB/Simulink对上述控制律进行仿真,仿真结果表明设计的准滑模调节控制律能使系统在较短的时间回到期望的工作状态,没有抖振现象,验证了该设计方法的有效性。Taking a class of aero-engine nonlinear model as the research object,the compensation algorithm is introduced based on the traditional sliding mode control to design the speed regulation control law.The stability of the closed-loop system was analyzed based on the generalized Gronwall-Bellman lemma.The boundary constraint rela-tionship of the state norm two norms under a certain initial value was given.The state variable norm boundary can be adjusted by selecting the control law parameters,so that the system is gradually stable to the equilibrium state.The above control law was simulated using MATLAB/Simulink.The simulation results show that the designed quasi-sliding mode control law can return the system to the expected working state in a short time,and there is no chattering phenomenon,which verifies the effectiveness of the design method.

关 键 词：滑模控制 小型涡扇发动机 动态补偿 非线性 广义贝尔曼一格朗沃尔引理 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计]