噪声与振动控制2012，Vol.32Issue(3)：29-33,71,6.DOI:10.3969/j.issn.1006-1355.2012.03.007
高超声速机翼非线性颤振特性分析
Nonlinear Flutter Characteristic Analysis of the Hypersonic Wings
罗青 1李东旭 1聂海涛 2周毅 2张一名2
作者信息
- 1. 国防科技大学航天与材料工程学院,长沙410073
- 2. 中国一航成都飞机设计研究所,成都610041
- 折叠
摘要
Abstract
The dynamic equation of a 2-dimentional hypersonic wing was derived by using the modified third order nonlinear piston theory. Both linear and nonlinear flutter boundary conditions were obtained through Hopf-bifurcation theory and directive numerical method respectively. The simulation results show that the effects of nonlinearities can delay or precede the appearance of limit cycles oscillations according to the system parameters.关键词
振动与波/非线性/高超声速机翼/极限环振荡/气动弹性Key words
vibration and wave/ nonlinear/ hypersonic wing/ limit cycles oscillations / aeroelasticity分类
数理科学引用本文复制引用
罗青,李东旭,聂海涛,周毅,张一名..高超声速机翼非线性颤振特性分析[J].噪声与振动控制,2012,32(3):29-33,71,6.
