噪声与振动控制

›› 2012, Vol. 32 ›› Issue (3): 29-33.DOI: 10.3969/j.issn.1006-1355.2012.03.007

• 2.振动理论与数值解法 • 上一篇    下一篇

高超声速机翼非线性颤振特性分析

罗青1，李东旭1,聂海涛2,周 毅2，张一名2   

  1. （ 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 ）
  • 收稿日期:2011-05-23 修回日期:2011-08-29 出版日期:2012-06-18 发布日期:2012-06-18
  • 通讯作者: 罗青

Nonlinear Flutter Characteristic Analysis of the Hypersonic Wings

LUO Qing 1,LI Dong-xu 1，NIE Hai-tao 2，ZHOU Yi 2，ZHANG Yi-ming 2   

  1. ( 1. National Univ. of Defense Technology, Changsha 410073, China;2. AVIC Chengdu Aircraft Design & Research Institute, Chengdu 610041, China )
  • Received:2011-05-23 Revised:2011-08-29 Online:2012-06-18 Published:2012-06-18
  • Contact: LUO Qing

摘要： 采用3阶修正活塞理论推导二元高超声速机翼的非线性气动弹性动力学方程。选取几组系统参数，分别通过求取系统特征值，得到线性颤振速度。以及在考虑非线性效应时，分析系统在不同流速下的动力学响应特性。数值仿真的结果表明系统的非线性效应可以延迟或提前极限环振荡的产生。

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

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.

Key words: vibration and wave, nonlinear, hypersonic wing, limit cycles oscillations, aeroelasticity

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