基于改进滑模趋近律的航空发动机控制器设计  

The Controller Design for Aero-engine Based on Improved Reaching Law of Sliding Mode Control

作　　者：刘帅[1] 王金环[2] 白杰 戴士杰[1] LIU Shuai;WANG Jin-huan;BAI Jie;DAI Shi-jie(School of Mechanical Engineering,Hebei University of Technology,Tianjin 300130,China;China School of Sciences,Hebei University of Technology,Tianjin 300130,China;Tianjin Key Laboratory for Civil Airworthiness and Maintenance,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]河北工业大学机械工程学院,天津300130 [2]河北工业大学理学院,天津300130 [3]中国民航大学天津市民用航空器适航与维修重点实验室,天津300300

出　　处：《科学技术与工程》2019年第34期408-413,共6页Science Technology and Engineering

基　　金：国家自然科学基金(71371186)资助

摘　　要：将多幂次滑模趋近律用于航空发动机控制,设计了基于滑模控制方法的航空发动机追踪控制器。针对多幂次滑模趋近律在航空发动机追踪控制中出现的高频振荡问题,提出了一种改进的多幂次滑模趋近律。基于改进多幂次滑模趋近律的追踪控制仿真表明,改进的多幂次滑模趋近律适用于航空发动机追踪控制,该方法不仅具备了多幂次滑模趋近方法响应速度快、鲁棒性好的优点,而且消除了控制中的高频振荡现象。An improved sliding mode control algorithm was applied to aeroengine control,for which the controller was designed that based on sliding mode control.An improved multi power reaching law of sliding mode control was proposed to reduce high frequency oscillation phenomenon appeared in multi power tracking control process of aero engine.The proposed reaching law was used in simulation of aero engine control system.The results show that the proposed reaching law is applicable for tracking control of aero engine.Not only does the proposed reaching law has these advantages that are fast response speed and strong robustness but also it can eliminate high frequency oscillation phenomenon.

关 键 词：航空发动机 滑模控制 趋近律 多幂次 

分 类 号：V233.73[航空宇航科学与技术—航空宇航推进理论与工程]