Buckling of Cylindrical Shells Subjected to Nonuniform Axial Loads

Abstract

The linear buckling problem of a cylindrical shell subjected to circumferentially varying axial edge loads or thermal loads is considered. The case of an oscillatory loading having a cosinusidal form with a single arbitrary harmonic index is treated first. Closed-form expressions for the critical eigenvalues are obtained, spanning the entire range of the harmonic index. Buckling modes are also presented. An interaction law among harmonic loadings based on existing numerical evidence is then postulated. This leads to the capability of calculating the buckling load for any given distribution. The method is compared, and good agreement is obtained, with published results on the heating of an axial strip. It is then used to calculate the buckling of a cylindrical shell subjected to a concentrated axial force.

Structural Behavior of Thin-Walled Metal Silos Subject to Different Flow Channel Sizes under Eccentric Discharge Pressures

“…This matches findings of earlier studies (e.g. Libai and Durban, 1973;1977;Cai, 2003). The reasons for this slight increase above this critical value are twofold.…”

A Study of Buckling in Column-Supported Cylinders

“…A simple general conclusion from this work on perfect shells might be that buckling occurs under a clrcumferentially non-uniform distribution of axial stress when the maximum stress Is similar to the classical elastic critical value for uniform axial compression. Libai and Durban [13] gave simple expressions which describe the increase in buckling stress above this simple rule, but the strength gains are generally small. These classical solutions are based on linear bifurcation analyses of perfect shells, though shells under local loads generally behave in a non-linear manner.…”

“…Despite the extensive research efforts on shell buckling in the last few decades, only a few studies [8][9][10][11][12][13] have examined the buckling behaviour of shells under circumferentially varying axial loads. A simple general conclusion from this work on perfect shells might be that buckling occurs under a clrcumferentially non-uniform distribution of axial stress when the maximum stress Is similar to the classical elastic critical value for uniform axial compression.…”

Parametric Instability of Doubly Curved Panels Subjected to Non-Uniform Harmonic Loading

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