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Delamination effects on the unsteady aero-elastic behavior of composite wing by modal analysis
Journal of Vibration and Control ( IF 2.8 ) Pub Date : 2021-06-07 , DOI: 10.1177/10775463211019213
Ali Reza Torabi 1 , Shahrokh Shams 2 , Mahdi Fatehi Narab 2 , Mohammadali Amiri Atashgah 2
Affiliation  

This article deals with the investigation of delamination effects on the flutter behavior of a composite wing subjected to unsteady aerodynamic loads by providing an integrated procedure using exact methods. For this purpose, an undamaged wing structure is modeled as a cantilevered Bernoulli–Euler beam with coupled bending–torsion and delaminated wing structure is modeled as three interconnected intact beams. The modal analysis of the intact and delaminated beams is performed and mode shapes are obtained based on the development of the dynamic stiffness matrix, a computer code and an iterative method. The fundamental modes of the intact and delaminated beam derived from the free vibration analysis are used in Galerkin’s method and the flutter and divergence speeds are obtained with aerodynamic forces applied. In fact, modified shape functions were developed to reflect the delamination effect in the aeroelastic analysis. Also, for the unsteady aeroelastic analysis, an iterative algorithm is developed. It was found that the delamination location and its length can have a positive or a negative influence on the flutter behavior of the wing which depends on the fiber angle.



中文翻译:

分层对复合材料机翼非定常气动弹性行为的模态分析

本文通过提供使用精确方法的集成程序,研究分层对承受非定常气动载荷的复合材料机翼颤振行为的影响。为此,未损坏的机翼结构被建模为悬臂式 Bernoulli-Euler 梁,带有耦合弯曲 - 扭转和分层的机翼结构被建模为三个相互连接的完整梁。基于动态刚度矩阵、计算机代码和迭代方法的发展,对完整梁和分层梁进行模态分析并获得模态振型。Galerkin 方法中使用了从自由振动分析导出的完整和分层梁的基本模式,并在施加空气动力的情况下获得颤振和发散速度。实际上,改进了形状函数以反映气动弹性分析中的分层效应。此外,对于非定常气动弹性分析,开发了迭代算法。发现分层位置及其长度会对机翼的颤振行为产生积极或消极的影响,这取决于纤维角度。

更新日期:2021-06-08
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