Buckling Characteristics of Symmetrically and Antisymmetrically Laminated Composite Plates with Central Cutout

Abstract

A numerical and experimental study was carried out to determine the effects of anti-symmetric laminate configuration, cutout and length/thickness ratio on the buckling behavior of E/glass-epoxy composite plates. The buckling loads were presented for symmetrically and anti-symmetrically laminated plates subjected to axial compression load. The study included two different laminate configurations ([90/45/−45/0] as and [90/45/−45/0] s ), two different cutout shapes (circular and semi-circular), two different length/thickness ratios (L/t=75 and 37.5) and three boundary conditions (clamped-clamped [CC], clamped-pinned [CP] and pinned-pinned [PP]). Firstly, the buckling loads of eight-ply E/glass-epoxy rectangular plates were determined experimentally. Then, the buckling loads of the laminated composites were calculated by ANSYS finite-element computer code. The changing in buckling load of the composites due to the presence of cutout and changing of length/ thickness ratio was calculated. Finally, the experimental test results were compared to the buckling loads of plates obtained from the finite element analysis.

Finite element simulation of buckling-induced failure of carbon fibre-reinforced laminated composite panels embedded with damage zones

“…To predict buckling strength of delaminated thin panels a single ply circular shaped damage is assumed such that buckling initiates instead of compressive failure occurring. In the cases of inserting a hole, soft inclusion, artificial damage zones, and softening stiffness authors reduced engineering material stiffness properties according to requirements of the problems [4]. Overall damage areas (circular-shaped) recorded during the impact testing of the actual carbon fibre/epoxy quasi-isotropic laminates clamped along their edges were within the range from 500-8800 (mm 2 ) in [21] as shown in column 5 of Table 3.…”

“…The internal damage growth induced buckling instabilities are greatly influenced by through-thethickness location, direction, shape, and size of damage [4]. Similarly, the impact damage of composite panels often is reported to be fairly uniform through-the-thickness that concentrates to a small region of damage width [5].…”

“…Simulations were performed for undamaged and damaged laminates. It was reported in[4] that the undamaged laminate could only fail either globally or under compression, they have proved to be difficult to fail in any other way than global buckling.…”

Effect of trapezoidal shapes and non-uniform edge loads on buckling behaviour of plates with cutouts

“…Subsequently, the independent variables selected were A, B, C, D and E, while the non-dimensional buckling load (c cr ) was chosen as the study's response (dependent variable). As suggested by the program, the final CCD acquired for the c cr with important terms was quadratic, and is given in equation (6).…”

A Parametric study on the effect of elliptical cutouts for buckling behavior of composite plates under non-uniform edge loads

“…Hence, a sound consciousness of buckling characteristic is necessary to design the laminated panel with cutout during the act of non-uniform edge loads. Jain and Kumar (2004); Ghannadpour et al (2006); Baba and Baltaci (2007); Kumar and Singh (2010) explored the buckling analysis of composite laminate plates with a central circular cutout under uniformly distributed uniaxial edge compression. Aydin Komur et al (2010) considered the elliptical cutout for analyzing buckling behaviour with woven glass polyester material.…”