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Instability of Integral Panels

Published online by Cambridge University Press:  28 July 2016

P. C. Dunne
P. C. Dunne*
Affiliation:
R.A.E. Technical College
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Extract

The paper by Dr. A. H. Chilver (October 1955 Journal) purposed “ to present alternative theoretical approaches to the problem of local instability of a simple type of panel with unflanged stiffeners.”

Examination of these alternative approaches reveals that they are in fact identical and are based on the same approximate representation of the buckled form of the plate by sinusoidally varying lengthwise and transverse deflection, and of the stiffener by sinusoidally varying twist. The difference in the results obtained by Dr. Chilver is explained by the fact that whereas in the first analysis he uses plate theory correctly to express the strain energy in the stiffener, in his second analysis he omits entirely the torsion-bending energy.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 59 , Issue 540 , December 1955 , pp. 853 - 854
Copyright
Copyright © Royal Aeronautical Society 1955

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References

1. Chilver, A. H. (1955). The Local Instability of a Simple Integral Panel. Journal of the Royal Aeronautical Society, October 1955.CrossRefGoogle Scholar
2. Argyris, J. H. and Dunne, P. C. (1952). Handbook of Aeronautics, Vol. 1—Structural Principles and Data. Part 2—Structural Analysis. Pitman and Royal Aeronautical Society, 1952.Google Scholar
3. Kelsey, S. (1955). Instability of Integral Panels. Journal of the Royal Aeronautical Society, October 1955.Google Scholar
4. Catchpole, E. J. (1954). The Optimum Design of Compression Surfaces having Unflanged Integral StifFeners. Journal of the Royal Aeronautical Society, Vol. 58. No. 527, p. 765, November 1954.Google Scholar