A Fluid-Structure Coupling Algorithm Based on Finite Element Method for Precise Analysis of Transonic and Supersonic Panel Flutter

doi:10.7652/xjtuxb201401013

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A Fluid-Structure Coupling Algorithm Based on Finite Element Method for Precise Analysis of Transonic and Supersonic Panel Flutter

更新时间：2025-07-09

- A Fluid-Structure Coupling Algorithm Based on Finite Element Method for Precise Analysis of Transonic and Supersonic Panel Flutter
- Vol. 48, Issue 1, Pages: 73-83(2014)
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201401013
  CLC： O323
- Online First：10 January 2014，
  
  Published：2014
- 稿件说明：
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A Fluid-Structure Coupling Algorithm Based on Finite Element Method for Precise Analysis of Transonic and Supersonic Panel Flutter[J]. 2014, 48(1): 73-83.
DOI：

A Fluid-Structure Coupling Algorithm Based on Finite Element Method for Precise Analysis of Transonic and Supersonic Panel Flutter[J]. 2014, 48(1): 73-83. DOI： 10.7652/xjtuxb201401013.

摘要

为了精确和定量分析超声速与跨声速壁板的颤振特性

提出了一种基于有限元方法的流-固耦合算法

并用其研究了二维壁板颤振问题。首先

给出了壁板的von Kármán几何大变形运动方程

以及高速气流的欧拉控制方程。然后

采用标准有限元方法对壁板方程进行空间离散

而对流动控制方程的离散则运用双时间步长推进的特征线分裂有限元方法

从而有效地消除了流场数值解的振荡问题。随后

采取松耦合算法实现了流体与固体间的数据传递。最后

运用所提出的算法对超声速和跨声速气流作用下壁板的气动弹性特性进行了分析

考察了归一化动压、预紧力和厚度比对系统特性的影响

并将该算法的分析结果与采用线性/非线性活塞理论和线性化势流理论的经典壁板颤振结果进行了对比

证明该算法可以在较宽广的马赫数范围内给出气动力的精确描述

尤其适合于分析跨声速气流下的壁板气动弹性响应。

Abstract

To analyze the supersonic and transonic panel flutter behavior quantitatively and accurately

a fluid-structure coupling algorithm based on the finite element method(FEM)is proposed for the two-dimensional panel flutter problem. First

the von Kármán's large deformation theory is adopted to model the panel

and the high speed air flow is approached by the Euler equations. Then

the equation of panel is discretized spatially by the standard FEM

and the equations of fluid are discretized by the characteristic-based split finite element method(CBS-FEM)with dual time stepping

thus the numerical oscillation often encountered in numerical simulation of fluid flow can be eliminated. Furthermore

a loose coupling algorithm is applied to the data exchange between the fluid and the structure. Finally

the proposed algorithm is used to investigate the aeroelastic behavior of the panel in supersonic and transonic air flows and the influences of the non-dimensional dynamic pressure

pre-tightening force and thickness ratio on the system. The results are compared with those of the classical panel flutter analyses using linear/nonlinear piston theory and linearized potential flow theory. It shows that the proposed algorithm enables to obtain accurate aerodynamic pressure in a wide range of Mach numbers

especially for the analysis of panel aeroelasticity in transonic air flows.

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Keywords

references

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