Analysis of anisotropic laminated cylindrical shells subjected to destabilizing loads. Part II: Numerical results

Stability analysis of cross-ply laminated shells of revolution using a curved axisymmetric shell finite element

“…The buckling pressures obtained for relatively thin cross-ply laminated cylinders under external lateral/hydrostatic pressure are found out to be in very good agreement with the results presented by Han and Simitses [34] and Shen and Li [35]. Cagdas and Adali [14], using the same shell theory, have reported good agreement (maximum error less than 10%) with the benchmark 3D elasticity based results for thick orthotropic cylinders under external hydrostatic pressure presented by Kardomateas [16].…”

“…Stability of a relatively thin simply supported cross-ply laminated cylinder under external pressure, q, was investigated by Han and Simitses [34] and Shen and Li [35]. The difference between the lateral and the hydrostatic pressure is that, in the lateral pressure case, the ends of the cylinder are not loaded.…”

Evaluation of non-linear buckling loads of geometrically imperfect composite cylinders and cones with the Ritz method

“…Cylinders with ܴ = 190.5 ݉݉, ܴ ℎ ⁄ = 30 and three ‫ܮ‬ ܴ ⁄ ratios are evaluated using 7 different laminates. Due to the similarity with the shell theory adopted the present model closely approaches the predictions of Han and Simitses [37]. In Table 9 the numerical and experimental results of Messager et al [39] and the predictions of Li and Lin [38] are compared with the present model (݉ ଵ = 150, ݉ ଶ = ݊ ଶ = 40), showing that for this moderately thick shell (ܴ ℎ ⁄ = 16.05) the CLPT differs from the finite element results by 5.5% and 3.3%, for the two laminates, respectively.…”

“…When these matrices are for each integration point only the stiffness matrix corresponding to the element containing this integration point has to be evaluated, whereas in the Ritz method the whole stiffness matrix has to be evaluated for each s of freedom are the amplitudes of the approximation functions of the field variables. Table 8 compares critical hydrostatic pressure obtained with the proposed model (݉ ଵ = 150, ݉ ଶ = ݊ ଶ = 40) with the analytical solution of Han and Simitses [37] and the model using a higher order shear deformation theory proposed by Li and Lin [38]. Cylinders with ܴ = 190.5 ݉݉, ܴ ℎ ⁄ = 30 and three ‫ܮ‬ ܴ ⁄ ratios are evaluated using 7 different laminates.…”

Finite element buckling analysis of rotationally periodic laminated composite shells

“…As Figure 8 shows, this is a buckling problem of a graphite epoxy-laminated cylindrical shell under lateral pressure. The boundary conditions are that the displacements u; v; w and bending moment are all equal to zero at the middle layer of z = 0 and z = L. The material properties are Note: Only E 11 ; E 22 ; G 12 and 21 are given in Reference [12]. To make the three-dimensional buckling analysis possible, we add E 33 ; G 31 ; G 23 ; 31 and 23 according to the transversely isotropic property of each ply.…”