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Some Observations on the Compressive Buckling of Rectangular Plates

Published online by Cambridge University Press:  07 June 2016

W. H. Wittrick
W. H. Wittrick*
Affiliation:
Department of Aeronautical Engineering, University of Sydney
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Summary

The problem considered is the buckling of a rectangular plate under uniaxial compression. The ends may be either both clamped, both simply-supported or a mixture of the two. The sides may be elastically restrained against both deflection and rotation with any stiffnesses whatsoever. It is shown that the curve of buckling stress coefficient versus side ratio can be deduced in a simple manner from that of a plate with the same end conditions but with both sides simply-supported, provided only that the buckling stress coefficient and wavelength for an infinite strip with the same side conditions are known. Some correlations between the curves for the three types of end condition are discussed. It is also shown that if, for some given side ratio, the buckling mode is known, then it is always possible to deduce the rate of change of buckling stress coefficient with side ratio at that point. The argument is based upon an assumption which is shown to give very accurate results in a wide range of cases.

Type
Research Article
Information
Aeronautical Quarterly , Volume 14 , Issue 1 , February 1963 , pp. 17 - 30
Copyright
Copyright © Royal Aeronautical Society. 1963

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References

1. Wittrick, W. H. Correlation Between Some Stability Problems for Orthotropic and Isotropic Plates under Bi-axial and Uni-axial Direct Stress. The Aeronautical Quarterly, Vol. IV, p. 83, 1952.Google Scholar
2. Timoshenko, S. Theory of Elastic Stability. First edition, p. 364. McGraw-Hill, 1936.Google Scholar
3. Levy, S. Buckling of Rectangular Plates with Built-in Edges. Journal of Applied Mechanics, Vol. 9, p. A–171, 1942.Google Scholar
4. Smith, R. C. T. The Buckling of Flat Plywood Plates in Compression. Report ACA-12, Australia, 1944.Google Scholar
5. Wittrick, W. H. and Bodley, W. E. Compressive Buckling of Infinite Strips with Elastically Restrained Edges. To be published in The Aeronautical Quarterly.Google Scholar