航空发动机自适应全局快速非奇异Terminal滑模控制  

Adaptive global fast non-singular Terminal sliding mode control for aero-engine

作　　者：苗卓广[1,2] 谢寿生 张波[3] 任立通[1] 王立国[1] 吴勇[4] 

机构地区：[1]空军工程大学航空航天工程学院 [2]中国人民解放军95961部队 [3]中国人民解放军61769部队 [4]中国人民解放军总参谋部陆航研究所

出　　处：《航空动力学报》2013年第11期2634-2640,共7页Journal of Aerospace Power

摘　　要：针对航空发动机控制系统须具有强鲁棒性和快速响应等特点及Terminal滑模控制存在奇异性等缺点,提出了一种航空发动机自适应全局快速非奇异Terminal滑模控制器设计方法.设计了一种快速非奇异Terminal滑模面,同时解决了传统Terminal滑模控制的奇异性和远离平衡点收敛速度慢两个缺点.采用自适应方法估计等效干扰,无需已知航空发动机的干扰上界,利用Lyapunov理论分析了其稳定性.仿真结果表明:设计的Terminal滑模控制器具有良好的动态性能,状态输出响应快速,调节时间在2s左右,无稳态误差,无超调,未发生奇异现象.A method for adaptive global fast nonsingular Terminal sliding mode control was put forward according to the characteristics of aeroengine＇s control system with the ro bustness and the capability of fast response as well as the singularity shortcoming of Termi nal sliding mode control. The devised fast nonsingular Terminal sliding surface solved these two problems of the singularity and the slow convergence speed when the sliding surface was far away the equilibrium point. Equivalent interferences were estimated by selfadaptive method without need to know the upper boundary of interferences of aeroengine. Then the stability was analyzed based on the theory of Lyapunov. Simulation results show that the de vised Terminal sliding mode controller has good dynamic performance; the response of stateoutput is fast, and the regulation time is about 2 s, without steady error, overshoot and singularity.

关 键 词：航空发动机 TERMINAL滑模控制 自适应控制 非奇异性 抖振 

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]