Abstract
A two-dimensional, curvilinear, isoparametric, finite element is used to provide a discrete layer analysis of deformations and stresses in stiffened, cross-ply composite cylinders subjected to thermal-mechanical loading. The generalized plane problem is analyzed by considering a discrete layer representation of a generic transverse cross section of the stiffened cylinder to provide the complete three-dimensional stale of stress. Individual layers of the cylinder and the stiffener are modeled explicitly, providing an accurate and detailed representation of deformations and stresses including interlaminar stresses. Cross-ply skins with cross-ply or unidirectional stiffeners are studied for fabrication-induced residual thermal effects, applied axial strain, torsion, and internal pressure loading. The analysis shows that local curvatures and interlaminar stress concentrations are present near the skin / stiffener joint. Interlaminar stresses are also present along the free edge of the stiffener.
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