Effect of lamination sequence on the localization and shear crippling instability in thick imperfect cross-ply rings under external pressure

Effects of thickness and fibre misalignment on compression fracture in cross-ply (very) long cylindrical shells under external pressure

“…These two extreme cases are (i) thin metallic cylindrical shells, which are characterized by the previously mentioned cellular shape in the circumferential direction with a large azimuthal number, and (ii) thick laminated advanced fibre reinforced composite rings (very long cylindrical shells), whose response is dominated by the interlaminar or transverse (primarily shear) deformation. Kim & Chaudhuri [35] have investigated the role of lamination sequence, in conjunction with modal imperfection in lowering the load-carrying capability of infinitely long thick laminated cross-ply cylindrical shells (plane strain rings) with linear material property. The appearance of a limit point on the elastic post-buckling equilibrium path has been found to be a measure of the effect of interlaminar shear/normal deformation on localization [31,35,36].…”

“…Kim & Chaudhuri [35] have investigated the role of lamination sequence, in conjunction with modal imperfection in lowering the load-carrying capability of infinitely long thick laminated cross-ply cylindrical shells (plane strain rings) with linear material property. The appearance of a limit point on the elastic post-buckling equilibrium path has been found to be a measure of the effect of interlaminar shear/normal deformation on localization [31,35,36].…”

“…These complexities and uncertainties relate to very fundamental questions pertaining to (i) linkage between macrostructural instability, such as buckling/postbuckling failure of a structural component, e.g. a ring or cylindrical shell at the geometric scale of at least several centimetres and larger [11,31,32,[35][36][37], and microstructural instability, such as kink band type failure at the fibre-matrix level (at the geometric scale of about 10 µm) investigated by Chaudhuri & Garala [10], Chaudhuri et al [12], Chaudhuri [6], Moran et al [38], Moran & Shih [39], Gutkin et al [40] and others. The nonlinear finite-element analysis (FEA) results [11,31,32,[35][36][37][41][42][43] pertaining to the appearance of a limit point on the equilibrium path that results in localization of the deformation pattern in and lowering of the load-carrying capability of laminated carbon/epoxy composite cylindrical shells and rings, demonstrate their extreme sensitivity to thickness shear, modal/local geometric imperfections as well as material nonlinearity ('yield' stress and strain hardening).…”

Effects of Surface-Parallel Edge Restraints and Inter-laminar Shear on the Responses of Doubly Curved General Cross-Ply Panels

“…Seventh, significant progress has been reported by Kim and Chaudhuri [10,14,20,[26][27][28]32], Hsia and Chaudhuri [11], Chaudhuri and Hsia [12,13], Chaudhuri and Kim [4,24,25,33,34], Tvergaard and Needleman [31], Chaudhuri [29][30][35][36][37][38]44,116], Chaudhuri, et al [45,46], and Chaudhuri and Abu-Arja [118], on large deflection, material nonlinearity, nonlinear resonance (eigenvalue), post-buckling, localization/delocalization, shear crippling type propagating instability, and compression fracture of composite shells/panels of cylindrical geometry. In future, we intend to extend such studies to laminated anisotropic doubly curved panels.…”

Review of Recent Literature on Static Analyses of Composite Shells: 2000-2010

“…Recent studies include Yuan et al [58] in which a stress projection, layer-wise-equivalent formulation was used for accurate predictions of transverse stresses in laminated plates and shells. Kim and Chaudhuri [59,60] and Chaudhuri and Kim [61] described a layer-wise linear displacement distribution theory and based their analysis on it to investigate the buckling and shear behavior of a long cross-ply cylindrical shell (ring). Leigh and Tafreshi [62] used layerwise shell finite element based on first order shear deformation theory to investigate delamination buckling of composite cylindrical shells.…”