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.
出处
《燃气轮机技术》
2015年第4期10-15,34,共7页
Gas Turbine Technology
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
aero-engine
adaptive sliding mode control（ASMC）
upper bound of uncertainties
adaptation law
tracking performance
