低音速气动弹性机翼的主动控制  

Active control of low-sonic velocity aeroelasticity wing

作　　者：仇磊[1] 

机构地区：[1]江苏科技大学电子信息学院,江苏镇江212003

出　　处：《电子设计工程》2015年第16期120-122,125,共4页Electronic Design Engineering

摘　　要：基于模糊滑模控制(FSMC)方法研究了低音速机翼颤振的主动控制。提出一种模糊滑模控制方法,主要解决非线性气动弹性的浮沉和俯仰二维机翼的颤振问题。根据气动弹性机翼,设计了滑模面,建立了模糊滑模控制器,控制器能有效抑制颤振。与自适应控制技术相比较,结果显示模糊滑模控制收敛性更好。The active control on flutter of low-sonic velocity wing is researched based on fuzzy sliding mode control method. The fuzzy sliding mode control method is proposed to solve the problems of flutter on nonlinear aeroelastic two-dimensional wing with plunge and pitch. According to aeroelasticity wing, the sliding surface is designed. Then fuzzy sliding controllers are established with effective control performance on flutter. Compared with adaptive control technology , the result shows that fuzzy sliding control method has better performance in astringency.

关 键 词：模糊滑模控制 主动控制 气动弹性机翼 颤振 

分 类 号：TN-9[电子电信]