Buckling analysis of fibre reinforced laminate with capsule shaped cut out for different ply orientation.

In the structural sectors of aviation, aerospace, and marine engineering, composite materials are widely used. It is a potential substitute for traditional metallic components due to its mechanical characteristics, which include low density, strength, and corrosion resistance. Specifically fibre reinforced laminated plates are used as structural members in aerospace vehicles due to its high strength to weight ratio and they are mostly subjected to compressive loads which leads to buckling of plate structures. Also there are chances of some unavoidable holes for the transfer of pipelines which makes the laminates unstable. For a set of parallel gas pipes, capsule shaped cutouts are made on the plate. So the variation of buckling strength is studied under different parameters. The buckling strength of the plane laminates with different ply orientation is calculated by implementing MATLAB code using classical laminate plate theory (CLPT), the results obtained is validated with the recent literature. Then the variation of buckling strength of the plate with capsule shaped cut out under different parameters like ply orientation, aspect ratio and cutout orientation is studied for carbon epoxy and glass epoxy combination. The composite laminate is numerically simulated using ANSYS ACP(Pre), and buckling analysis is performed with the help of Eigen value buckling module. The variation of the buckling strength under the set of parameters is plotted. The buckling strength variation for the hybrid laminate for above mentioned parameter set up is also obtained. Among the various combinations, C/G/G/C combination of hybrid laminate shows maximum buckling strength and among the ply directions [0/45]₂ gives the best buckling strength. [ABSTRACT FROM AUTHOR]