Analysis of anisotropic laminated cylindrical shells subjected to destabilizing loads. Part I: Theory and solution procedure

Simitses, George J.; Han, Byoungkee

doi:10.1016/0263-8223(91)90021-p

Cited by 16 publications

(6 citation statements)

References 23 publications

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“…In the above two examples, the numerical critical loads are both slightly smaller than analytical ones. This is because the transverse shear deformation is assumed to be linear in Reference [11], while there is no such assumption in the three-dimensional FE buckling analysis. The small discrepancy between the numerical and analytical results shows that the combination of rotationally periodic FE buckling analysis method and the new relative DOF element is a suitable numerical strategy for this kind of problem.…”

Section: Cylindrical Shells Under Lateral Pressurementioning

confidence: 99%

Finite element buckling analysis of rotationally periodic laminated composite shells

Xiang

Xue

Liu

et al. 2001

Numerical Meth Engineering

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SUMMARYA ÿnite element (FE) buckling analysis of rotationally periodic laminated composite shells is performed in this paper. Because the buckling mode of such structures is characterized as rotationally periodic, a corresponding FE buckling analysis scheme is proposed to reduce the computational expenses. Moreover, a new kind of relative degrees-of-freedom element is developed, which can be connected to other solid elements with ease and can yield satisfactory results with a relatively coarse FE mesh. Numerical results of two laminated cylindrical shells subjected to lateral pressure are compared with theoretical ones. The good agreement of them shows the validity of this new computational strategy. Finally, a practical structure is analysed to demonstrate the advantage of this method.

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Section: Cylindrical Shells Under Lateral Pressurementioning

confidence: 99%

Finite element buckling analysis of rotationally periodic laminated composite shells

Xiang

Xue

Liu

et al. 2001

Numerical Meth Engineering

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“…This effect was considered in a number of studies referred in [3,18]. However, such shells, either isotropic or orthotropic, displayed a considerable disagreement between experiment and theory.…”

mentioning

confidence: 96%

“…It is obvious that the thickness of a ply in a composite cannot be less than the diameter of a fiber, and the thickness of a shell in various products is limited. Therefore, it is necessary to develop methods for solving problems of shell theory, including problems of the nonlinear deformation and stability of composite shells, based on a more general model of composite with the minimum degree of symmetry.In [18,19], it was shown, experimentally and numerically (FEM), that a cylindrical shell made by winding four plies ( , ) + -j j s onto a cylindrical mandrel buckles in a mode with dents tilted toward the axis, i.e., twists, when loaded only along the axis. This effect was considered in a number of studies referred in [3,18].…”

mentioning

confidence: 99%

“…In [18,19], it was shown, experimentally and numerically (FEM), that a cylindrical shell made by winding four plies ( , ) + -j j s onto a cylindrical mandrel buckles in a mode with dents tilted toward the axis, i.e., twists, when loaded only along the axis. This effect was considered in a number of studies referred in [3,18].…”

mentioning

confidence: 99%

“…The monograph [3] outlines solutions to some problems of the nonlinear deformation and stability of laminated shells of zero Gaussian curvature and shells of negative curvature subject to a combination of tension, bending, and torsion because of the structural unbalance of the laminate. The models used in [18][19][20][21] are based on the Kirchhoff-Love theory of anisotropic shells, as in [3,10]. An important factor affecting the critical loads of not very thin composite shells is low transverse-shear stiffness.…”

mentioning

confidence: 99%

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The Theory of Stability of Cylindrical Composite Shells Revisited

2015

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A method for the stability analysis of laminated cylindrical shells with anisotropy due to plies with one plane of symmetry is developed. The governing system of differential equations is derived using the Timoshenko hypotheses for displacements. The dependence of the critical loads on the orientation, number, thickness, and transverse shear stiffness of plies under axial compression is studied Introduction. Cylindrical composite shells are widely used in various modern structures. In many cases, shells are in such conditions that the compressive stresses induced in them may reach critical levels. These critical stresses can be calculated or measured in preliminary tests. There are methods for the stability analysis of composite shells based on mathematical models of various accuracy [1][2][3][4][5][6][7]9]. Irrespective of the kinematic and equilibrium equations, most studies use a structural idealization of a composite with three planes of symmetry. This is justified by the fact that laminated shells are made so as to correct for the anisotropy due to the misalignment between the ply orientation and the shell axes. The angles of plies are so alternated that the internal stresses in them are counterbalanced. This method is known [3,20] to work if the number of plies tends to infinity, and the ply thickness tends to zero. It is obvious that the thickness of a ply in a composite cannot be less than the diameter of a fiber, and the thickness of a shell in various products is limited. Therefore, it is necessary to develop methods for solving problems of shell theory, including problems of the nonlinear deformation and stability of composite shells, based on a more general model of composite with the minimum degree of symmetry.In [18,19], it was shown, experimentally and numerically (FEM), that a cylindrical shell made by winding four plies ( , ) + -j j s onto a cylindrical mandrel buckles in a mode with dents tilted toward the axis, i.e., twists, when loaded only along the axis. This effect was considered in a number of studies referred in [3,18]. However, such shells, either isotropic or orthotropic, displayed a considerable disagreement between experiment and theory. The initial postcritical behavior and the sensitivity to imperfections of anisotropic shells were studied in [3,[15][16][17] using the asymptotic Koiter method [11,12]. The monograph [3] outlines solutions to some problems of the nonlinear deformation and stability of laminated shells of zero Gaussian curvature and shells of negative curvature subject to a combination of tension, bending, and torsion because of the structural unbalance of the laminate. The models used in [18][19][20][21] are based on the Kirchhoff-Love theory of anisotropic shells, as in [3,10]. An important factor affecting the critical loads of not very thin composite shells is low transverse-shear stiffness.To solve the problem of the stability of anisotropic composite shells, we will use the Timoshenko-Mindlin theory of shells. We will obtain an analytic solution in the form of co...

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Optimally reinforced cutouts in laminated circular cylindrical shells

Şenocak

Waas

1996

International Journal of Mechanical Sciences

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Analysis of anisotropic laminated cylindrical shells subjected to destabilizing loads. Part I: Theory and solution procedure

Cited by 16 publications

References 23 publications

Finite element buckling analysis of rotationally periodic laminated composite shells

Finite element buckling analysis of rotationally periodic laminated composite shells

The Theory of Stability of Cylindrical Composite Shells Revisited

Optimally reinforced cutouts in laminated circular cylindrical shells

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