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Buckling and postbuckling analysis of stiffened composite panels in axial compression.

机译：加筋复合板在轴向压缩下的屈曲和屈曲后分析。

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The major objective of this study is to analyze buckling and delamination behavior of composite stiffened panels subjected to axial compression.; First, a combined analytical and experimental study of a blade stiffened composite panel subjected to axial compression was conducted. The effects of the differences between a simple model used to design the panel and the actual experimental conditions were examined. It was found that in spite of many simplifying assumptions the design model did reasonably well in that the experimental failure load was only 10% higher than the design load. Several structural analysis programs, including PANDA2, STAGS, and ABAQUS, were used to obtain high fidelity analysis results. The buckling loads from STAGS agreed well with the experimental failure loads. However, substantial differences were found in the out-of-plane displacements of the panel. Efforts were made to identify the source of these differences. Implementing non-uniform load introduction with general contact definition in the STAGS finite element model improved correlation between the measured and predicted out-of-plane deformations.; Next, a new method called Crack Tip Force Method (CTFM) is derived for computing point-wise energy release rate along the delamination front in delaminated plates. The CTFM is computationally simple as the G is computed using the forces transmitted at the crack-tip between the top and bottom sub-laminates and the sub-laminate properties.; Finally, buckling and postbuckling of a blade-stiffened composite panel under axial compression with a partial skin-stiffener debond are investigated. Two different finite element models, where nodes of the panel skin and the stiffener flange are located on the mid-plane or at the interface between skin and flange, are used. Linear buckling analysis is conducted using both STAGS and ABAQUS. Postbuckling analysis is conducted with STAGS. Comparison between the present results and previous buckling analysis results show a good correlation. Buckling analysis results for various stiffener geometries and debond ratios are presented.
机译：这项研究的主要目的是分析承受轴向压缩的复合加劲板的屈曲和分层行为。首先，对叶片加筋的复合板进行轴向压缩进行了综合的分析和实验研究。检查了用于设计面板的简单模型与实际实验条件之间差异的影响。结果发现，尽管进行了许多简化的假设，但设计模型的表现还是相当不错的，因为实验失败载荷仅比设计载荷高10％。几个结构分析程序（包括PANDA2，STAGS和ABAQUS）用于获得高保真度分析结果。 STAGS的屈曲载荷与实验失效载荷非常吻合。但是，发现面板的平面外位移存在很大差异。努力找出这些差异的根源。在STAGS有限元模型中采用一般接触定义实施非均匀载荷引入，改善了实测和预测平面外变形之间的相关性。接下来，推导了一种称为“裂纹尖端力法”（CTFM）的新方法，用于计算分层板沿分层前沿的逐点能量释放速率。 CTFM计算简单，因为 G 是使用在顶部和底部子层压板以及子层压板特性之间的裂纹尖端传递的力来计算的。最后，研究了叶片加筋的复合板在轴向压缩下具有部分表皮加劲剂脱胶的屈曲和后屈曲。使用了两种不同的有限元模型，其中面板蒙皮和加劲肋的节点位于中平面或蒙皮与翼缘之间的界面处。使用STAGS和ABAQUS进行线性屈曲分析。后屈曲分析使用STAGS进行。当前结果与先前屈曲分析结果之间的比较显示出良好的相关性。给出了各种加劲肋几何形状和脱骨率的屈曲分析结果。

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