Vibration and Buckling Analysis of Composite Plate Using FEA

Abstract

In order to achieve a numerical solution to the governing differential equations, the finite element technique, also known as FEM, is used. The buckling analysis of rectangular laminated plates with rectangular cross-sections is explored for a variety of boundary condition and aspect ratio combinations. Buckling loads are analysed and verified with respect to other works that may be found in the relevant body of literature in order to establish whether or not the current method is accurate. The trustworthiness of the finite element approach that was used is shown by the substantial agreement with the other data that was provided. New numerical findings have been developed for uniaxial and biaxial compression loads on symmetrically laminated composite plates. These results concentrate on the important impacts of buckling for a variety of factors, including boundary condition, aspect ratio, and modular ratio. It was discovered that the influence of boundary conditions on buckling load rises as the aspect ratio increases for both uniaxial and biaxial compression loading. This was the case regardless of whether the loading was uniaxial or biaxial. It was also discovered that, at larger values of elastic modulus ratio, the variation of buckling load with aspect ratio becomes virtually constant.

Introduction

The text presents a comprehensive review of the mechanical behavior of laminated composite plates, with a primary focus on buckling, post-buckling, vibration, and failure analysis. It emphasizes that linear buckling analysis alone is insufficient to describe the true load-carrying capacity of composite plates, as laminated composites can sustain loads significantly higher than the critical buckling load during post-buckling due to their layered structure. Understanding post-buckling behavior is therefore essential for safe and efficient structural design.

The study highlights various failure mechanisms in laminated composites—such as matrix cracking, fiber breakage, debonding, and delamination—and stresses the importance of predicting first-ply failure, damage progression, and ultimate load capacity under both in-plane and out-of-plane loading conditions.

A detailed vibration analysis review summarizes classical and modern analytical, numerical, and finite-element approaches used to determine natural frequencies and mode shapes of laminated composite plates. Prior research employing Ritz methods, isogeometric analysis, finite element models, and piezoelectric-based vibration control is discussed, demonstrating the complexity and accuracy required for dynamic analysis.

The text further examines buckling analysis considering orthotropic material behavior, noting that composites are particularly susceptible to buckling under in-plane compressive loads. Experimental and numerical investigations are emphasized as necessary to complement theoretical models.

An extensive literature review highlights recent studies addressing buckling and vibration behavior under varying conditions, including cutouts, boundary conditions, material orientations, and advanced numerical techniques such as ANN prediction, NURBS-based isogeometric methods, and higher-order finite element formulations.

Finally, the document outlines the mathematical formulation and finite element modeling of laminated composite plates, discussing classical, first-order, and higher-order shear deformation theories. It concludes that accurate buckling prediction requires advanced models that account for transverse shear deformation and interlaminar stress continuity, as traditional plate theories may overestimate buckling loads and compromise structural safety.

Conclusion

In order to predict the buckling response of symmetric cross-ply rectangular laminates subjected to uniaxial and biaxial compression, a finite element analysis that is founded on classical laminate theory is utilized. An explanation is given for the effect that the boundary condition, aspect ratio, and elastic modulus ratio have on the buckling load. It has been discovered that the plate\'s resistance to buckling improves as additional constraints are applied to it. Also, the buckling load will decrease as the modulus ratio increases, and it will become almost constant as the elastic modular ratio is increased to higher values.

References

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Copyright

Copyright © 2026 Kapil Raje , Laxmi Jonwar , Manoj Kumar Saxena, Dileep Gangil. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.