Abstract
The bubHing of laminated composite cylindrical shell panels subjected to transverse load is investigated. The geometrical non-linear analysis is carried out using thefinite element method based o,n a higher-order shear deformation theory. An eight nodded degenerated isoparametric shell element with nine degrees of freedom at each node is considered. The geometric non-linear behaviour and the collapse pressures ere presented for symmetrically and antisymmetrically laminated cross-ply and angle-ply cylindrical shell panels subiected to uniform normal pressure.
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