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Buckling of Oblique Plates with Clamped Edges Under Uniform Shear

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

In a previous paper the author derived, by the Rayleigh-Ritz method, a determinantal equation for obtaining the critical magnitude of any uniform system of edge stress applied to a clamped oblique plate. In the present paper this equation is used to derive values for the buckling stresses of clamped oblique plates subjected to pure shear along and perpendicular to two edges of the plate.

As would be expected, it is found that reversal of the direction of the shear produces a change in the critical value. The lower value occurs when the shear is tending to increase the obliquity of the plate and critical values corresponding to this direction are calculated for 45° oblique plates with side ratios varying between 3/5 and 5/3. The critical values obtained for the reverse direction were obviously very inaccurate, due to the inadequacy of the series which was used to represent the buckling mode. As yet no satisfactory method has been found for overcoming this difficulty.

Type
Research Article
Information
Aeronautical Quarterly , Volume 5 , Issue 1 , May 1954 , pp. 39 - 51
Copyright
Copyright © Royal Aeronautical Society. 1954

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References

1. Wittrick, W. H. (1953). Buckling of Oblique Plates with Clamped Edges under Uniform Compression. Aeronautical Quarterly, Vol. IV, February 1953.Google Scholar
2. Iguchi, S. (1933). Eine Lösung für die Berechnung der biegsamen rechteckigen Platten. Julius Springer, Berlin, 1933.Google Scholar
3. Southwell, R. V. and Skan, S. W. (1924). On the Stability under Shearing Forces of a Flat Elastic Strip. Proc. Roy. Soc. A, Vol. 105, 1924, p. 582.Google Scholar
4. Budiansky, B. and Connor, R. W. (1948). Buckling Stresses of Clamped Rectangular Flat Plates in Shear. N.A.C.A. T.N. 1559, 1948.Google Scholar
5. Guest, J. (1951). The Buckling of Uniformly Compressed Parallelogram Plates having all Edges Clamped. Report No. SM.172, Aeronautical Research Laboratories, Melbourne, June 1951.Google Scholar
6. Anderson, R. A. (1951). Charts giving Critical Compressive Stress of Continuous Flat Sheet divided into Parallelogram-Shaped Panels. N.A.C.A. T.N. 2392, July 1951.Google Scholar