Effect of Edge Restraint on the Buckling of Axially Compressed Circular Cylindrical Shells

Abstract

A broad analytical study of the effect of edge restraint on the buckling stress of geometrically perfect, axially compressed circular cylindrical shells, based on linear elastic theory, is presented. An overall evaluation of this effect is made by studying the 16 limiting cases, 7 of which are studied for the first time, it is found that 8 permit buckling to occur at stresses less than the classical theoretical value of theory and experiments indicate that the effect of shell length on the buckling stress can usually be disregarded is used in the analysis. This fact suggests that shells may be assumed to be semi-infinite; as a consequence, formulas for buckling stresses are determined in essentially closed form.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1970
Accession Number
AD0873254

Entities

People

  • L. W. Rehfield

Organizations

  • Stanford University

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  • Air Platforms
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  • Physics

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  • Structural Dynamics.