航空发动机自适应滑模控制方法的比较研究  

Comparative Research on Adaptive Sliding Mode Control in Aero-engine

作　　者：孙晖[1,2] 刘尚明[1] 邓奇超 

机构地区：[1]清华大学热能工程系热科学与动力工程教育部重点实验室,北京100084 [2]中国航空工业集团公司航空动力控制系统研究所,江苏无锡214063 [3]中国船舶重工集团公司第701研究所,武汉430064

出　　处：《燃气轮机技术》2015年第4期10-15,34,共7页Gas Turbine Technology

摘　　要：为了解决航空发动机参数随工况变化大、不确定性上界未知的控制问题,采用三种不同的方法设计自适应滑模控制器,通过参数自适应律的设计,使滑模控制增益随系统运行条件改变而变化。通过仿真比较了三种设计方法在航空发动机线性模型稳态点的控制效果和转速跟踪性能。结果表明,采用第3种自适应滑模控制方法的系统线性响应迅速,超调小,转速跟踪能力强,波形基本无失真,综合控制性能最好。In order to solve the controlling problems of varying parameters and unknown upper bound of uncertainties under wide opera- tion conditions in aero-engine, three different adaptive sliding mode control methods were studied. In the paper, adaptation laws were designed to modify switch gain as conditions changed. The control effect was tested at linear steady-state points of the aero-engine mod- el and the tracking performance was compared. The simulation results indicate that the third ASMC obtains a faster system response and smaller overshoot, compared with the other two methods. Furthermore, it has strong tracking ability without waveform distortion, so it achieves the best integrated controlling performance.

关 键 词：航空发动机 自适应滑模控制 不确定性上界 自适应律 跟踪性能 

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]