摘要
间隙非线性机翼系统在一定速度范围内会发生极限环振荡,传统线性控制律对极限环抑制效果通常不显著且鲁棒性不足,因此,需设计相应的非线性控制律来提高系统的控制效果及鲁棒性。通过对间隙非线性二元翼段气动弹性系统进行线性二次调节(LQR)控制律设计,结果显示:极限环速度范围由11.4~16.9 m/s优化至12.9~19.2 m/s。同时,对间隙非线性二元翼段气动弹性系统进行滑模控制律(SMC)设计,结果显示:极限环速度范围由11.4~16.9 m/s优化至29.4~39.3 m/s。算例结果表明:针对间隙非线性系统,所设计SMC效果优于LQR控制律。
Limit cycle oscillation happens in airfoil systems with freeplay nonlinearity within a specific velocity range.Because the traditional linear control law’s limit cycle suppression effect is typically insignificant and its robustness is insufficient,a corresponding nonlinear control law must be designed in order to improve the system’s control effect and robustness.According to this article,the limit cycle speed range is optimized between 11.4-16.9 m/s and 12.9-19.2 m/s.The linear quadratic regulartor(LQR)control law is created for the 2D airfoil aeroelastic system with freeplay nonlinearity.At the same time,the sliding mode control law(SMC)is designed for the 2D airfoil aeroelastic system with freeplay nonlinearity above,it shows that the speed range of the limit cycle is optimized from 11.4-16.9 m/s to 29.4-39.3 m/s.The result of the calculating example shows that the SMC law is better than that of LQR for nonlinear systems in this paper.
作者
王诗其
张征
宋晨
杨超
郑焱午
WANG Shiqi;ZHANG Zheng;SONG Chen;YANG Chao;ZHENG Yanwu(COMAC Beijing Aircraft Technology Research Institute,Beijing 102211,China;School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China)
出处
《北京航空航天大学学报》
北大核心
2025年第6期2033-2040,共8页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金(11402013)。
关键词
间隙非线性
极限环振荡
控制律
线性二次调节
滑模控制律
freeplay nonlinearity
limit cycle oscillation
control law
linear quadratic regulator
sliding mode control law
