| 航空发动机自适应全局快速非奇异Terminal滑模控制 |
| |
| 引用本文： | 苗卓广,谢寿生,张波,任立通,王立国,吴勇.航空发动机自适应全局快速非奇异Terminal滑模控制[J].航空动力学报,2013,28(11):2634-2640. |
| |
| 作者姓名： | 苗卓广 谢寿生 张波 任立通 王立国 吴勇 |
| |
| 作者单位： | 空军工程大学 航空航天工程学院, 西安 710038;中国人民解放军95961部队, 北京 100195;空军工程大学 航空航天工程学院, 西安 710038;中国人民解放军61769部队, 山西 吕梁 032100;空军工程大学 航空航天工程学院, 西安 710038;空军工程大学 航空航天工程学院, 西安 710038;中国人民解放军 总参谋部 陆航研究所, 北京 101121 |
| |
| 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.
|
| 关 键 词： | 航空发动机 Terminal滑模控制 自适应控制 非奇异性 抖振 |
| 收稿时间： | 2012/11/1 0:00:00 |
Adaptive global fast non-singular Terminal sliding mode control for aero-engine |
| |
| MIAO Zhuo-guang,XIE Shou-sheng,ZHANG Bo,REN Li-tong,WANG Li-guo and WU Yong.Adaptive global fast non-singular Terminal sliding mode control for aero-engine[J].Journal of Aerospace Power,2013,28(11):2634-2640. |
| |
| Authors: | MIAO Zhuo-guang XIE Shou-sheng ZHANG Bo REN Li-tong WANG Li-guo and WU Yong |
| |
| Institution: | Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;The Unit 95961, the Chinese People's Liberation Amay, Beijing 100195, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;The Unit 61769, the Chinese People's Liberation Army, LÜliang Shanxi 032100, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Army Aviation Research Institute, the Headquarters of the General staff, the Chinese People's Liberation Army, Beijing 101121, China |
| |
| Abstract: | A method for adaptive global fast non-singular Terminal sliding mode control was put forward according to the characteristics of aero-engine's control system with the robustness and the capability of fast response as well as the singularity shortcoming of Terminal sliding mode control. The devised fast non-singular 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 self-adaptive method without need to know the upper boundary of interferences of aero-engine. Then the stability was analyzed based on the theory of Lyapunov. Simulation results show that the devised Terminal sliding mode controller has good dynamic performance;the response of state output is fast, and the regulation time is about 2s, without steady error, overshoot and singularity. |
| |
| Keywords: | aero-engine Terminal sliding mode control adaptive control non-singularity chattering |
|
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
