複合材料積層円筒殻の軸圧縮座屈に及ぼす積層構成効果

概要

論文の詳細を見る
Advanced fiber-reinforced composite materials have been used for structural members in aeronautical and astronautical fields, because of their high specific strength and stiffness. In general, composite laminated structures behave differently from homogeneous orthotropic ones due to the coupling effect that is caused by the anisotropy and the unsymmetric lamination, except for the case of symmetric cross-ply laminates. In this paper, such coupling effects on the buckling stress in the cross-ply and angle-ply laminated cylindrical shells under axial compression are discussed. That is, the effects of lamination constitution, stacking sequence, number of layers, lamination angle and dimension of cylinders, on the buckling value are analysed assuming the buckling pattern which satisfy the equilibrium equation based on the Flugge-type expressions.