Nonlinear Analysis of Transverse Shear Deformable Laminated Composite Cylindrical Shells—Part II: Buckling of Axially Compressed Cross-Ply Circular and Oval Cylinders

1992 ◽  
Vol 114 (1) ◽  
pp. 110-114 ◽  
Author(s):  
K. P. Soldatos
Keyword(s):  
Transverse Shear ◽  
Shell Theory ◽  
Cylindrical Shells ◽  
Laminated Composite ◽  
Companion Paper ◽  
Buckling Loads ◽  
Simply Supported ◽  
Laminated Composite Shells ◽  
Shear Deformable ◽  
Oval Cylindrical Shells

A linearized transverse shear deformable shell theory presented in a companion paper is confined to consideration with the buckling problem of axially compressed, cross-ply laminated noncircular cylindrical shells. Based on a solution of its governing differential equations, obtained for simply supported shells by means of Galerkin’s method, a study of the buckling problem of axially compressed circular and oval cylindrical shells, of a regular antisymmetric cross-ply laminated arrangement, is presented. Moreover, by comparing the numerical results obtained with corresponding results based on a classical Love-type shell theory, the combined influence of both the transverse shear deformation and the shell eccentricity on the buckling loads of such laminated composite shells is examined.

Nonlinear Analysis of Transverse Shear Deformable Laminated Composite Cylindrical Shells—Part I: Derivation of Governing Equations

1992 ◽  
Vol 114 (1) ◽  
pp. 105-109 ◽  
Author(s):  
K. P. Soldatos
Keyword(s):  
Transverse Shear ◽  
Cylindrical Shells ◽  
Laminated Composite ◽  
Companion Paper ◽  
Governing Equations ◽  
Initial Stress State ◽  
Static And Dynamic Analysis ◽  
Highly Nonlinear ◽  
Nonlinear Static ◽  
Shear Deformable

Based on the concept of an “intermediate” class of deformations, a theory suitable for the nonlinear static and dynamic analysis of transverse shear deformable circular and noncircular cylindrical shells, composed of an arbitrary number of linearly elastic monoclinic layers, is developed. The theory is capable of satisfying zero shear traction boundary conditions at the inner and outer shell surfaces. Upon assuming that the shell is subjected to a certain initial stress state and applying the highly nonlinear governing equations derived to the adjacent equilibrium criterion, a set of Love-type linearized equations is further derived. These latter equations are suitable for buckling and/or vibration analyses; in a companion paper, they are solved and used for the study of the influence of transverse shear deformation on the buckling loads of axially compressed cross-ply laminated circular and oval cylindrical shells.

Elasticity Solutions for Laminated Orthotropic Cylindrical Shells Subjected to Localized Longitudinal and Circumferential Moments

2003 ◽  
Vol 125 (1) ◽  
pp. 26-35 ◽  
Author(s):  
K. Bhaskar ◽  
N. Ganapathysaran
Keyword(s):  
Differential Equations ◽  
Ordinary Differential Equations ◽  
Shell Theory ◽  
Cylindrical Shells ◽  
Laminated Composite ◽  
Two Dimensional ◽  
Simply Supported ◽  
Elasticity Solutions ◽  
Laminated Composite Shells ◽  
Taylor’S Series

The purpose of this work is to present baseline elasticity solutions for laminated composite shells subjected to localized moments. For simply supported cross-ply cylindrical shells, the problem reduces to one of coupled ordinary differential equations which are solved in terms of Taylor’s series. Results, in the form of tables and graphs, are presented for the cases of longitudinal and circumferential moments. These results would be very useful for judging the accuracy of approximate two-dimensional shell theories. They are used herein to study the errors of a shell theory based on the classical Love-Kirchhoff hypothesis.

Buckling of Stiffened Curved Panels and Cylindrical Shells: A Study of Comparison Among Various Theories

2012 ◽  
Author(s):  
S. Harutyunyan ◽  
D. J. Hasanyan ◽  
R. B. Davis
Keyword(s):  
Cylindrical Shell ◽  
Circular Cylindrical Shell ◽  
Cylindrical Shells ◽  
Laminated Composite ◽  
Physical Parameters ◽  
Buckling Loads ◽  
Isotropic Cylindrical Shell ◽  
Analytical Formulas ◽  
Laminated Composite Shells ◽  
Curved Panels

Formulation is derived for buckling of the circular cylindrical shell with multiple orthotropic layers and eccentric stiffeners acting under axial compression, lateral pressure, and/or combinations thereof, based on Sanders-Koiter theory. Buckling loads of circular cylindrical laminated composite shells are obtained using Sanders-Koiter, Love, and Donnell shell theories. These theories are compared for the variations in the stiffened cylindrical shells. To further demonstrate the shell theories for buckling load, the following particular case has been discussed: Cross-Ply with N odd (symmetric) laminated orthotropic layers. For certain cases the analytical buckling loads formula is derived for the stiffened isotropic cylindrical shell, when the ratio of the principal lamina stiffness is F = E2/E1 = 1. Due to the variations in geometrical and physical parameters in theory, meaningful general results are complicated to present. Accordingly, specific numerical examples are given to illustrate application of the proposed theory and derived analytical formulas for the buckling loads. The results derived herein are then compared to similar published work.

Buckling of Shear Deformable Antisymmetric Angle-Ply Laminated Cylindrical Panels Under Axial Compression (Design Paper)

1992 ◽  
Vol 114 (3) ◽  
pp. 353-357 ◽  
Author(s):  
K. P. Soldatos
Keyword(s):  
Flat Plate ◽  
Axial Compression ◽  
Transverse Shear ◽  
Shell Theory ◽  
Laminated Composite ◽  
Cylindrical Panel ◽  
Buckling Behavior ◽  
Cylindrical Panels ◽  
Shear Deformable ◽  
Design Paper

This paper deals with the buckling problem of antisymmetric angle-ply laminated circular cylindrical panels subjected to a uniform axial compression. Since a flat plate configuration occurs as a particular case of the cylindrical panel geometry (zero shallow angle parameter), the corresponding flat plate problem is studied as a particular case of the problem considered. The theoretical analysis is based on a nonlinear theory developed in a previous paper (Soldatos, 1992), which accounts for parabolically distributed transverse shear strains through the shell thickness. The linearized differential equations, governing the buckling behavior of a simply supported panel, are solved on the basis of Galerkin’s method. Comparisons of corresponding numerical results, based on both the refined shell theory employed and a classical Love-type shell theory, show the influence of transverse shear deformation on the buckling loads of such laminated composite panels.

Effects of Axial Imperfections on Vibrations of Anti-Symmetric Cross-Ply, Oval Cylindrical Shells

1986 ◽  
Vol 53 (3) ◽  
pp. 675-680 ◽  
Author(s):  
David Hui ◽  
I. H. Y. Du
Keyword(s):  
Vibration Mode ◽  
Cylindrical Shells ◽  
Homogeneous Material ◽  
Fundamental Vibration ◽  
Geometric Imperfections ◽  
Simply Supported ◽  
Fundamental Frequencies ◽  
Young’S Moduli ◽  
Wave Numbers ◽  
Oval Cylindrical Shells

This paper examines the effects of axial geometric imperfections on the fundamental vibration frequencies of cross-ply simply-supported oval cylindrical shells. It is found that the presence of such imperfection with small amplitudes may significantly raise or lower the fundamental frequencies, depending on the wave numbers of the imperfection and vibration mode. The effects of oval eccentricity, bending-stretching coupling of the material, the reduced-Batdorf parameter and Young’s moduli ratio are examined. It appears that the present problem has not been examined, even in the simplified case of oval cylindrical shells made of isotropic-homogeneous material.

Forced Motions of Elastic Cylindrical Shells

1975 ◽  
Vol 42 (2) ◽  
pp. 321-325 ◽  
Author(s):  
C. C. Huang
Keyword(s):  
Boundary Value Problem ◽  
Shell Theory ◽  
Initial Conditions ◽  
Formal Solution ◽  
Cylindrical Shells ◽  
Time Dependent ◽  
Axially Symmetric ◽  
Symmetric Motion ◽  
Simply Supported ◽  
Acceleration Method

A formal solution is presented for the dynamic boundary-value problem of the axially symmetric motion of finite, Timoshenko-type, isotropic, linearly elastic, cylindrical shells with time-dependent boundary conditions of any admissible combination, acted upon by time-dependent surface tractions with specified arbitrary initial conditions, obtained by using Herrmann-Mirsky shell theory and modal acceleration method. The method is applied to a simply supported shell subject to longitudinal tensile step forces at both ends. The transient response is studied in detail and the results predicted by the improved and the classical theories are compared.

Effect of Ring Support Position and Geometrical Dimension on the Free Vibration of Ring-Stiffened Cylindrical Shells

2014 ◽  
Vol 580-583 ◽  
pp. 2879-2882
Author(s):  
Xiao Wan Liu ◽  
Bin Liang
Keyword(s):  
Cylindrical Shell ◽  
Free Vibration ◽  
Shell Theory ◽  
Cylindrical Shells ◽  
Ritz Method ◽  
Geometrical Dimension ◽  
Stiffened Cylindrical Shell ◽  
Simply Supported ◽  
Ring Support ◽  
Stiffened Cylindrical Shells

Effect of ring support position and geometrical dimension on the free vibration of ring-stiffened cylindrical shells is studied in this paper. The study is carried out by using Sanders shell theory. Based on the Rayleigh-Ritz method, the shell eigenvalue governing equation is derived. The present analysis is validated by comparing results with those in the literature. The vibration characteristics are obtained investigating two different boundary conditions with simply supported-simply supported and clamped-free as the examples. Key Words: Ring-stiffened cylindrical shell; Free vibration; Rayleigh-Ritz method.

On the Effect of Transverse Shear Deformability on Stress Concentration Factors for Twisted and Sheared Shallow Spherical Shells

1986 ◽  
Vol 53 (3) ◽  
pp. 597-601 ◽  
Author(s):  
E. Reissner ◽  
F. Y. M. Wan
Keyword(s):  
Stress Concentration ◽  
Transverse Shear ◽  
Shell Theory ◽  
Bessel Functions ◽  
Plate Theory ◽  
Modified Bessel Functions ◽  
Spherical Shells ◽  
Concentration Factors ◽  
Stress Concentration Factors ◽  
Shear Deformable

Explicit solutions are obtained, in terms of modified Bessel functions, for the problems of transverse twisting and of tangential shearing of transversely shear-deformable shallow spherical shells with a small circular hole. The relevant stress concentration factors are calculated for the entire range of a rise-to-thickness ratio parameter and a transverse shear deformability parameter. The modification of known results obtained previously by shear deformable plate theory, and by shallow shell theory without consideration of transverse shear deformation effects, is delineated.

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