Abstract
The solution for the buckling problem of composite laminates is usually based on the assumption that the panels are subjected to uniform edge loads without any discontinuity or damage. Nevertheless, in practice, the panels are provided with various sized opening subjected to non-uniform edge loads. Hence in this work, a finite element analysis is carried out to study the buckling behaviour of composite laminates with various sized elliptical openings under non-uniform edge loads. In the FE formulation, the panels are discretised by adopting 9-noded heterosis element and incorporating the effect of shear deformation and rotary inertia. The correctness of the formulation is validated by correlating the results with available literature. The influence of different sized elliptical cutouts on the buckling behaviour is investigated under the compressive and tensile type of non-uniform in-plane edge loads. The effect of various parameters such as cutout size, ply-orientation, ellipse-orientation, boundary condition and panel thickness is included in this work. It is observed from this work that the elliptical vertical cutout has higher buckling resistance as compared to that of the elliptical horizontal cutout.
Highlights
A laminated composite comes under the class of thin-walled structure, which are regularly found in several engineering fields, especially in the field of the aerospace industry
The panel with vertical elliptical cutout shows highest buckling resistance as compared to that of horizontal elliptical cutout only in the case of compressive loading conditions, whereas it is reversed in the case of tensile loading conditions
Angle-ply laminates are preferable over cross-ply laminates irrespective of elliptical cutout orientations, cutout sizes and loading conditions
Summary
A laminated composite comes under the class of thin-walled structure, which are regularly found in several engineering fields, especially in the field of the aerospace industry. Rajanna et al (2016a) studied the effect of partial load on the composite stiffened plate In such an instance, the stress distributions are likewise non-uniform. Aydin Komur et al (2008) and Chandra et al (2020a, 2020b, 2021) analysed the buckling behaviour of composite laminate under non-uniform varying in-plane compressive loads with circular cutouts. A very few literature covered the effect of circular and/or square cutouts subjected to compression and/or tension-type of non-uniform edge loads. A comprehensive study on the compression and tension buckling behaviour of composite laminates with different sized and oriented elliptical cutout under the consequence of various kinds of non-uniform edge loads is very much essential. A parametric study is carried out to investigate the effect of cutout size, ply-orientation, orientation of elliptical cutout, boundary condition and panel thickness under non-uniform compressive and tensile edge loads
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