Buckling analysis of laminated composite plates using an efficient C0 FE model

Abstract

Buckling analysis of laminated composite plates is carried out by using an efficient C 0 FE model developed based on higher order zigzag theory. In this model the first derivatives of transverse displacement have been treated as independent variables to overcome the problem of C 1 continuity associated with the FE implementation of the plate theory. The C 0 continuity of the present FE model is compensated in the stiffness matrix calculations by using penalty parameter approach. Numerical results and comparison with other existing solutions show that the present model is very efficient in predicting the buckling responses of laminated composites.

Assessment of inverse trigonometric zigzag theory for stability analysis of laminated composite and sandwich plates

“…The table indicates clearly that the evaluated results based on ITZZT are in well agreement with the elasticity results [2] and with the other compared results specifically with ZZ results [18,19]. As of fact, the equivalent single layer theories (ESL) over predict the buckling loads for laminated composite and sandwich plates.…”

“…The non-dimensional buckling loads are evaluated for different aspect ratios (a=b¼ 0.5, 1, 2) with the variation in span thickness ratios ranging from 100 to 5 and are jotted down in Table 3 along with the ZZ results of Singh and Chakrabarti [19]. A well agreement of present results with the other results [18] is observed.…”

“…All the evaluated results based on ITZZT are tabulated in Table 1 along with the exact results [2] and with the published results based on various theories. The HSDT results obtained by Kant and Manjunatha [23], Reddy and Phan [7], global local higher order theory (GLHT) results published by Matsunaga [24] and Lo et al [25], ZZ results demonstrated by Pandit et al [18] and Singh and Chakrabarti [19] are also included in the table for the necessary comparison purpose.…”

“…Buckling of laminated sandwich plates based on an improved higher order zigzag theory was studied by Pandit et al [18] considering the core compressibility effect. Singh et al [19] studied the buckling analysis of laminated composite and sandwich plates using finite element procedure based on a higher order zigzag theory derived by the same author. Khandelwal et al [20] employed a nine noded quadratic element to investigate the free vibration and buckling analysis of laminated composite and sandwich plate.…”

A C0 zig-zag model for the analysis of angle-ply composite thick plates

“…The same technique has been extended to analyze the vibration of sandwich plates with random material properties [23] and stochastic free vibration of soft-core sandwich plates [24]. By using the method of artificial constraints, Singh and Chakrabarti [25] proposed a C 0 finite element model based on the zig-zag theory to study the buckling of laminated composite plates. Khandelwal et al [26] also employed the assumed variables to replace the first derivatives of transverse displacement in the zig-zag model.…”