Buckling Behavior of Composite Plates

The buckling behaviour of composite plates arises from the interplay of material anisotropy and structural geometry under compressive and thermal loads. Composite laminates, typically fabricated from alternating plies of high-strength fibres and polymeric resins, exhibit directional stiffnesses that influence their resistance to out-of-plane deformations. Classical laminate plate theory and refined models such as first-order shear deformation theory provide analytical predictions of critical loads and associated mode shapes, while numerical approaches including finite element analysis yield detailed insights where complex boundary conditions, cut-outs or stiffening elements are present. The critical buckling load, defined as the smallest eigenvalue solving the stability problem, is affected by fibre orientation, ply stacking sequence, boundary support, aspect ratio and the presence of discontinuities. Thermal loading and non-uniform edge forces further modify pre-buckling stress distributions, leading to coupled buckling-vibration phenomena. Understanding these interactions is essential for lightweight design in aerospace, automotive and civil engineering, where the optimisation of weight, strength and damage tolerance must balance against the risk of sudden instability. Recent advances in hybridisation of fibre–metal laminates, topology optimisation for cut-outs, and multiscale modelling have driven improvements in reliability and performance of composite plate structures.

Research from Nature Portfolio

No recent Nature Portfolio content available.

Buckling Behavior of Composite Plates publication trend

The graph below shows the total number of articles in buckling behavior of composite plates across all publications each year (not limited to Nature Index journals).

Technical terms

Critical buckling load: The minimum compressive or thermal load at which a plate becomes unstable and exhibits a sudden deflection mode.

Anisotropy: Direction-dependent material behaviour arising from the alignment of fibres within composite laminates.

Laminate stacking sequence: The ordered arrangement of ply orientations in a composite plate, determining overall stiffness and stability.

First-order shear deformation theory: A refined plate theory accounting for transverse shear strains, improving buckling predictions for thick laminates.

Finite element method: A numerical technique dividing a structure into discrete elements to compute stress, deformation and stability characteristics.

References

1. Effects of different interlaminar hybridization and localized edge loads on the vibration and buckling behavior of fiber metal composite laminates. Composites Part C Open Access (2021).
2. Influence of Trapezoidal Shapes and Cutout Sizes on the Buckling Behaviour of Composite Laminates Under Thermally Induced Loads. Latin American Journal of Solids and Structures (2021).
3. A Parametric study on the effect of elliptical cutouts for buckling behavior of composite plates under non-uniform edge loads. Latin American Journal of Solids and Structures (2020).