Akademik Veri Yönetim Sistemi
THIN-WALLED STRUCTURES, cilt.223, 2026 (SCI-Expanded, Scopus)
Laminated composite cylindrical panels are widely used in aerospace, marine, and civil structures due to their high strength-to-weight efficiency; however, their stability and vibration characteristics can be markedly altered by porosity, foundation interaction, and realistic non-uniform in-plane edge loadings. This study presents a unified vibration and buckling formulation for porous orthotropic laminated cylindrical panels resting on orthotropic Pasternak foundations and subjected to parabolic, sinusoidal, and linearly varying edge compressions. A higher-order shear deformation theory (HSDT) is adopted to capture transverse shear effects without shear correction factors, and porosity is represented through uneven through-thickness distributions. The pre-buckling stress resultants for non-uniform edge loads are obtained exactly via the Airy stress function, and the governing equations derived from Hamilton's principle are reduced using the Galerkin method. The results demonstrate that the orthotropic Pasternak foundation substantially elevates both the fundamental frequency and the critical buckling load, with the maximum enhancement occurring when the foundation stiff axis is aligned with the panel longitudinal direction. Increasing porosity reduces stiffness and thus lowers the frequency and buckling resistance, whereas a sufficiently stiff foundation effectively compensates for this degradation. Moreover, increasing the material orthotropy ratio improves vibration performance but may reduce buckling capacity due to shear-dominated instability mechanisms. Finally, non-uniform edge compressions, particularly triangular distributions, can produce critical buckling loads up to two times those under uniform compression, underscoring the necessity of incorporating load non-uniformity and foundation orthotropy in reliable design.