Puranik, A.M.Kaliveeran, V.2026-02-032025Journal of Aeronautics, Astronautics and Aviation, 2025, 57, 7, pp. 1595-160119907710https://doi.org/10.6125/JoAAA.202507_57(7S).08https://idr.nitk.ac.in/handle/123456789/20633This study investigates the accuracy of Euler’s theory for predicting the critical buckling load of a laminated plate comprising a 2.4 mm steel core sandwiched between 1.3 mm aluminum layers, with dimensions 500 mm × 100 mm. Analytical solutions are based on Euler's buckling theory. The theoretical values are verified through ANSYS simulation and experimental testing. The results reveal the limitations of classical buckling assumptions when applied to laminated composites, emphasizing the effects of material heterogeneity. Numerical and experimental analyses confirm the influence of these factors on the critical load, providing insights into the adaptation of classical theory for complex material systems. This research offers a comprehensive framework for the buckling mechanism of laminates, bridging theoretical, computational, and experimental approaches. © 2025 The Aeronautical and Astronautical Society of the Republic of China. All rights reserved.AluminumAluminum coated steelBucklingBuckling behaviorBuckling loadsBuckling modesLaminated compositesLocal bucklingAluminum layersBuckling theoryCritical buckling loadsEuler bucklingEuler’s buckling theoryExperimental and numerical studiesLaminated plateS-theorySteel coreSteel-aluminum sandwichLaminating