The solution for the buckling problem of composite laminates is usually based on the assumption that the panels aresubjected to uniform edge loads without any discontinuity or damage. Nevertheless, in practice, the panels areprovided with various sized opening subjected to non-uniform edge loads. Hence in this work, a finite element analysisis carried out to study the buckling behaviour of composite laminates with various sized elliptical openings under nonuniform edge loads. In the FE formulation, the panels are discretised by adopting 9-noded heterosis element andincorporating the effect of shear deformation and rotary inertia. The correctness of the formulation is validated bycorrelating the results with available literature. The influence of different sized elliptical cutouts on the bucklingbehaviour is investigated under the compressive and tensile type of non-uniform in-plane edge loads. The effect ofvarious parameters such as cutout size, ply-orientation, ellipse-orientation, boundary condition and panel thickness isincluded in this work. It is observed from this work that the elliptical vertical cutout has higher buckling resistance ascompared to that of the elliptical horizontal cutout.
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