Elastic buckling analysis of laminated composite plates with through-the-width delamination using EAS solid element

Park, Dae Yong; Chang, Suk Yoon; Yhim, Sung-Soon

doi:10.1007/bf02823368

Cited by 4 publications

(1 citation statement)

References 31 publications

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“…The influence of the sectional stiffness of U-shaped ribs on the buckling modes and strengths of laminated composite plates are studied by Choi et al (2012) and Park (2006). Buckling behaviour of stiffened laminated plates using a layer-wise finite element formulation is studied by Guo et al (2002).…”

Section: Introductionmentioning

confidence: 99%

Buckling Analysis of Curvilinearly Stiffened Composite Panels with Cracks

Jrad

Khan

Kapania

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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S TIFFENERS attached to composite panels may significantly increase the overall buckling load of the resultant stiffened structure. First, buckling analysis of a composite panel with attached longitudinal stiffeners under compressive loads is performed using Ritz method with trigonometric functions. Results are then compared to those from ABAQUS FEA for different shell elements. The case of composite panel with one, two, and three stiffeners is investigated. The effect of the distance between the stiffeners on the buckling load is also studied. The variation of the buckling load and buckling modes with the stiffeners' height is investigated. It is shown that there is an optimum value of stiffeners' height beyond which the structural response of the stiffened panel is not improved and the buckling load does not increase. Furthermore, there exist different critical values of stiffener's height at which the buckling mode of the structure changes. Next, buckling analysis of a composite panel with two straight stiffeners and a crack at the center is performed. Finally, buckling analysis of a composite panel with curvilinear stiffeners and a crack at the center is also conducted. ABAQUS is used for these two examples and results show that panels with a larger crack have a reduced buckling load. It is shown also that the buckling load decreases slightly when using higher order 2D shell FEM elements.

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Section: Introductionmentioning

confidence: 99%