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Research Papers

Stability and Vibration Behavior of Composite Cylindrical Shell Panels Under Axial Compression and Secondary Loads

[+] Author and Article Information
J. Girish

Department of Civil Engineering, Bapatla Engineering College, Bapatla 522101, Indiagirisẖiitkgp@yahoo.co.in

L. S. Ramachandra

Department of Civil Engineering, IIT, Kharagpur 721302, Indialsr@civil.iitkgp.ernet.in

J. Appl. Mech 75(4), 041007 (May 13, 2008) (11 pages) doi:10.1115/1.2910772 History: Received November 30, 2006; Revised February 03, 2008; Published May 13, 2008

The nonlinear static response and vibration behavior of cross-ply laminated cylindrical shell panels subjected to axial compression combined with other secondary loading are examined. The shell theory adopted in the present case is based on a higher-order shallow shell theory, includes geometric imperfection and von Kármán-type geometric nonlinearity. The solutions to the governing nonlinear partial differential equations are sought using the multiterm Galerkin technique. The nonlinear equilibrium paths through limit points and bifurcation points are traced using the Newton–Raphson method coupled with the Riks approach. The free vibration frequencies of post-buckled cylindrical panels about the static equilibrium state are reported by solving the associated linear eigenvalue problem. Results are presented for simply supported cross-ply laminated cylindrical shell panels, which illustrates the influence of initial geometric imperfection, temperature field, lateral pressure loads, and mechanical edge loads on the static response and vibration behavior of the shell panel.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Geometry of cylindrical shell panel

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Figure 2

Comparison of one-term, three-term and four-term solutions for the post-buckling behavior of a composite cylindrical shell panel [0∕90∕0] under uniaxial edge compression

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Figure 3

The influence of initial geometric imperfections on the post-buckling behavior of composite cylindrical shell panel under uniaxial edge compression

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Figure 4

The influence of shear deformation on the post-buckling behavior of composite cylindrical shell panel under uniaxial edge compression

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Figure 5

The influence of shear deformation on the fundamental frequencies of composite cylindrical shell panel under uniaxial edge compression

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Figure 6

The influence of span-to-thickness ratio on the nonlinear behavior of cross-ply cylindrical shell panel under uniform lateral pressure

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Figure 7

The influence of span-to-thickness ratio on the fundamental frequencies of symmetric cross-ply cylindrical shell panel under uniform lateral pressure

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Figure 8

The influence of biaxial edge load on the post-buckling behavior of symmetric cross-ply cylindrical shell panel

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Figure 9

The influence of biaxial edge load on the fundamental frequencies of cross-ply cylindrical shell panel

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Figure 10

The influence of uniform lateral pressure and bi axial edge load on post-buckling behavior of cross-ply cylindrical shell panel

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Figure 11

The influence of uniform lateral pressure and biaxial edge load on fundamental frequencies of cross-ply cylindrical shell panel

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Figure 12

The influence of uniform through-thickness temperature and biaxial edge load on post-buckling behavior of cross-ply cylindrical shell panel

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Figure 13

The influence of uniform through-thickness temperature and biaxial edge load on fundamental frequencies of cross-ply cylindrical shell panel

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