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The Buckling and Bending of Orthotopic Sandwich Panels With All Edges Simply-Supported

Published online by Cambridge University Press:  07 June 2016

J. R. Robinson
J. R. Robinson*
Affiliation:
Handley Page Limited
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Summary

A formula is derived for the buckling in compression of an orthotropic sandwich panel, with all edges simply-supported. Two special types of symmetrical sandwiches, that of a sandwich having zero core flexural stiffnesses and of a corrugated core sandwich, are considered, and curves giving the critical buckling end load per inch are presented. An approximate theory is also given for the bending of sandwich panels under the action of an axial compressive load and a uniform lateral pressure. Curves are presented giving the maximum bending moments in a corrugated core sandwich panel.

Type
Research Article
Information
Aeronautical Quarterly , Volume 6 , Issue 2 , May 1955 , pp. 125 - 148
Copyright
Copyright © Royal Aeronautical Society. 1955

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References

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