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.

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.

Post-buckling Behavior of Stiffened Cross-Ply Cylindrical Shells

1994 ◽  
Vol 61 (4) ◽  
pp. 998-1000 ◽  
Author(s):  
M. Savoia ◽  
J. N. Reddy
Keyword(s):  
Axial Compression ◽  
Carrying Capacity ◽  
Shell Theory ◽  
Load Carrying Capacity ◽  
Imperfection Sensitivity ◽  
Buckling Modes ◽  
Geometric Imperfection ◽  
Buckling Behavior ◽  
Load Carrying ◽  
Post Buckling

The post-buckling of stiffened, cross-ply laminated, circular determine the effects of shell lamination scheme and stiffeners on the reduced load-carrying capacity. The effect of geometric imperfection is also included. The analysis is based on the layerwise shell theory of Reddy, and the “smeared stiffener” technique is used to account for the stiffener stiffness. Nu cylinders under uniform axial compression is investigated to merical results for stiffened and unstiffened cylinders are presented, showing that imperfection-sensitivity is strictly related to the number of nearly simultaneous buckling modes.

Modal analysis of cylindrical panels at elevated temperatures under nonuniform heating conditions: Experimental investigation

2020 ◽  
pp. 095440622093673
Author(s):  
CM Twinkle ◽  
C Nithun ◽  
Jeyaraj Pitchaimani ◽  
Vasudevan Rajamohan
Keyword(s):  
Free Vibration ◽  
Elevated Temperatures ◽  
Laminated Composite ◽  
Free Vibration Analysis ◽  
Cylindrical Panel ◽  
Experimental Results ◽  
Mode Shapes ◽  
Experimental Investigations ◽  
Nonuniform Heating ◽  
Cylindrical Panels

In this study, experimental investigations carried out to analyze the influences of different in-plane temperature variations on buckling and free vibration responses of metal and fiber-reinforced laminated composite cylindrical panels are presented. Initially, critical buckling temperature is calculated then free vibration analysis is performed as a function of the buckling temperature to analyze the changes in the natural frequencies and mode shapes. Experimental results revealed that the thermal buckling strength of the panel is significantly influenced by the nature of the heating condition. Similarly, significant changes in free vibration mode shapes are observed with the rise in temperature and also according to the heating conditions. It is also observed that, with the increase in temperature, nodal and anti-nodal lines of free vibration modes shifting towards the heating source. The experimental results are compared with the numerical simulation for the studies on the isotropic cylindrical panel and both the results are in good agreement.

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.

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.

scholarly journals Post-Buckling Behaviour of laminated Cylindrical Panels with/without Cut-Outs

2019 ◽  
Vol 8 (3) ◽  
pp. 8026-8030
Keyword(s):  
Compressive Load ◽  
Laminated Composite ◽  
Cylindrical Panel ◽  
Buckling Load ◽  
Equilibrium Path ◽  
Cylindrical Panels ◽  
Post Buckling ◽  
The Impact ◽  
Generalized Finite Element ◽  
Composite Cylindrical Panel

Buckling and post-buckling analysis of isotropic and laminated composite cylindrical plates/panels under compressive load has been done by equilibrium path approach (arc-length technique). The impact of cut outs on buckling and post-buckling load of an isotropic and laminated composite cylindrical plates/panels has been assessed by utilizing summed up generalized finite element programming ANSYS. In post-buckling Eigen mode imperfection shape is picked for creating geometric undulations on cylindrical panels with/without circular cut-outs. The impact of the area and size of the cut out and furthermore the composite utilize point on the buckling load of laminated composite cylindrical panel is explored with simply supported boundary conditions. The post-buckling consequences of laminated cylindrical panels have been validated with existing appropriate writing (18) and are additionally stretched out for analysis of sheets/plates with cutouts. It has been seen that the as the curvature of the panel increases load bearing capacity is increasing irrespective of the material and with/without cut out.

Buckling Behavior of Optimal Laminated Composite Cylindrical Shells Subjected to Axial Compression and External Pressure

2011 ◽  
Vol 121-126 ◽  
pp. 48-54 ◽  
Author(s):  
Behzad Abdi ◽  
Hamid Mozafari ◽  
Ayob Amran ◽  
Roya Kohandel ◽  
Ali Alibeigloo
Keyword(s):  
Axial Compression ◽  
Optimization Design ◽  
Cylindrical Shells ◽  
Laminated Composite ◽  
Optimization Procedure ◽  
Imperialist Competitive Algorithm ◽  
External Pressure ◽  
Design Variables ◽  
Buckling Behavior ◽  
Composite Cylindrical Shells

In this study, the buckling behavior of optimum laminated composite cylindrical shells subjected to axial compression and external pressure are studied. The cylindrical shells are composed of multi orthotropic layers that the principal axis gets along with the shell axis (x). The number of layers and the fiber orientation of layers are selected as optimization design variables with the aim to find the optimal laminated composite cylindrical shells. The optimization procedure was formulated with the objective of finding the highest buckling pressure. The Genetic Algorithm (GA) and Imperialist Competitive Algorithm (ICA) are two optimization algorithms that are used in this optimization procedure and the results were compared. Also, the effect of materials properties on buckling behavior was analyzed and studied.

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