基于模态耦合方法的机翼颤振数值模拟  

Numerical Simulation of Wing Flutter Based on Modal Coupled Method

作　　者：李中武[1] 曹平宽[1] 周天孝[1] 

机构地区：[1]中国航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2008年第1期43-46,共4页Aeronautical Computing Technique

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。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, the flutter predictions performed on an AGARD 445.6 wing at different Mach numbers are selected to highlight the validity and applied value of the methods in the paper.

关 键 词：颤振 模态耦合 颤振动压 阻尼率 AGARD445.6 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]