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Buckling and Vibration of Isosceles Triangular Plates having the Two Equal Edges Clamped and the Other Edge Simply–Supported

Published online by Cambridge University Press:  28 July 2016

Hugh L. Cox  and
Bertram Klein
Hugh L. Cox
Affiliation:
Douglas Aircraft Company Inc.
Bertram Klein
Affiliation:
Douglas Aircraft Company Inc.
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Extract

Approximate Solutions obtained by the method of collocation are presented for the lowest critical buckling load of an isosceles triangular plate loaded as shown in Fig. 1. Also, the fundamental frequency is given. The base of the triangle is simply supported and the other equal edges are clamped. The usual assumptions regarding the bending of thin plates are made. The governing differential equation for the plate loaded as shown in Fig. 1 is

1

where D is the plate stiffness, N is axial load per unit length, w is deflection, positive downward, and the quantities a and h are dimensions shown in Fig.1.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 59 , Issue 530 , February 1955 , pp. 151 - 152
Copyright
Copyright © Royal Aeronautical Society 1955

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References

1. Klein, B. and Cox, H. L. (1954). Approximate Structural Analysis by the Method of Collocation. Journal of the Aeronautical Sciences, Vol. 21, No. 10, p. 719, October 1954.Google Scholar
2. Wittrick, W. H. (1953). Buckling of a Right–Angled Isosceles Triangular Plate in Combined Compression and Shear. Department of Supply, Research and Development Branch, ARL/SM 220, Melbourne, November 1953.Google Scholar
3. Salvadori, M. G. (1951). Numerical Computation of Buckling Loads by Finite Differences. Transactions of the American Society of Civil Engineers, Vol. 116, pp. 590–624, 1951.CrossRefGoogle Scholar