BUCKLING RESPONSE OF QUASI-STATIC COMPRESSIVE LOADING OF SIX LAYERS CROSS-PLY LAMINATED COMPOSITE MATERIAL

Channaveerayya; Mahesh; Basavaraj Patil

BUCKLING RESPONSE OF QUASI-STATIC COMPRESSIVE LOADING OF SIX LAYERS CROSS-PLY LAMINATED COMPOSITE MATERIAL

Authors: Channaveerayya, Mahesh, Basavaraj Patil

Unique Paper ID: 182394
Volume: 11
Issue: 4
PageNo: 1758-1764

Keywords: Cut-out Composite plate Buckling load Quasi-static compressive load cross-ply laminated.

Abstract:
A numerical test of the buckling response of quasi-static compressive loading on six layers of cross-ply laminated composite material [0 degrees, 90 degrees, and 0 degrees] with centrally square and circular cutouts has been carried out in this work. Additionally, a finite element analysis has been performed in conjunction with the computational test. The computational methods were used in order to determine the connection between the size of the cut-out form and the buckling load. The buckling loads that were acquired through the numerical were compared with the literature results that were produced via the use of an ANSYS simulation software. There seems to be a high degree of concordance between the numerical findings. The buckling load of the composite plate has been seen to have reduced as the size of the cutout has increased. This is something that has been observed. The load of the cross-ply laminated composite plates is significantly impacted by a number of factors, including the cutout area, the cutout ratio (d/w), the weight of the fibers, the thickness of the plate, and the form of the fibers.

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ISSN: 2349-6002
Volume: 11
Issue: 4
PageNo: 1758-1764

BUCKLING RESPONSE OF QUASI-STATIC COMPRESSIVE LOADING OF SIX LAYERS CROSS-PLY LAMINATED COMPOSITE MATERIAL

Available:https://ijirt.org/Article?manuscript=182394

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