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Buckling of Tapered Rectangular Plates in Compression

Published online by Cambridge University Press:  07 June 2016

W. H. Wittrick  and
C. H. Ellen
W. H. Wittrick
Affiliation:
Department of Aeronautical Engineering, University of Sydney
C. H. Ellen
Affiliation:
Department of Aeronautical Engineering, University of Sydney
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Summary

The problem considered is the buckling of a rectangular plate, tapered in thickness in a direction parallel to two sides, and uniformly compressed in that direction. Curves are presented showing the variation of buckling stress coefficient with the side ratio and the amount of taper, for each of two types of thickness variation, namely exponential and linear, and for each of two sets of boundary conditions, namely all edges simply-supported, and ends clamped and sides simply-supported. It is shown that, unlike the case of a uniform plate, there are no discontinuous changes of buckling mode.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 13 , Issue 4 , November 1962 , pp. 308 - 326
Copyright
Copyright © Royal Aeronautical Society. 1962

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References

Note on page 311 * Henceforth the word “sides” will denote the edges y=0, b, while the word “ends” will denote the edges x=0,a.