| 基于模态耦合方法的机翼颤振数值模拟 |
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| 引用本文： | 李中武,曹平宽,周天孝.基于模态耦合方法的机翼颤振数值模拟[J].航空计算技术,2008,38(1):43-46. |
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| 作者姓名： | 李中武 曹平宽 周天孝 |
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| 作者单位： | 中国航空计算技术研究所,陕西,西安,710068 |
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| 摘 要： | 针对机翼气动弹性问题,发展了一种流固耦合模拟技术,将固体结构的广义位移表示为结构固有模态的线性组合,求解结构的运动,再与流体进行数据耦合、迭代计算.同时为了确定机翼颤振边界,发展了一种线性插值确定颤振边界方法.采用标准气弹机翼AGARD445.6算例,验证所采用的模态耦合技术和颤振边界确定方法的有效性及工程实用意义.
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| 关 键 词： | 颤振 模态耦合 颤振动压 阻尼率 AGARD445.6 |
| 文章编号： | 1671-654X(2008)01-0043-04 |
| 修稿时间： | 2007年9月18日 |
Numerical Simulation of Wing Flutter Based on Modal Coupled Method |
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| LI Zhong-wu,CAO Ping-kuan,ZHOU Tian-xiao.Numerical Simulation of Wing Flutter Based on Modal Coupled Method[J].Aeronautical Computer Technique,2008,38(1):43-46. |
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| Authors: | LI Zhong-wu CAO Ping-kuan ZHOU Tian-xiao |
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| Abstract: | In this paper a new method to simulate the fulid-structure interaction is proposed for aeroelastic problems during wing design,The generalized displacement of structure can be denoted as a linear combination of structure inherent modals by this method.This strategy solves the equations of motion that govern the structural dynamics of the wing,then couples fluid solution and structure solution in every time step.In addition,a linear interposition method is used to establish flutter boundary rapidly.Finally,t... |
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| Keywords: | wing flutter modal couple flutter dynamic pressure damping ratio AGARD445 6 |
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