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高超声速机翼非线性颤振特性分析

Nonlinear Flutter Characteristic Analysis of the Hypersonic Wings
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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。 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.
作者 罗青 李东旭 聂海涛 周毅 张一名
机构地区 国防科技大学航天与材料工程学院 中国一航成都飞机设计研究所
出处 《噪声与振动控制》 CSCD 2012年第3期29-33,71,共6页 Noise and Vibration Control
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 vibration and wave nonlinear hypersonic wing limit cycles oscillations aeroelasticity
分类号 O322 [理学—一般力学与力学基础]
  • 相关文献

参考文献9

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二级参考文献9

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共引文献5

噪声与振动控制
2012年 第3期

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