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An Energy Solution to the Buckling of Rectangular Plates Under Non-Uniform In-Plane Loading

Published online by Cambridge University Press:  04 July 2016

M. B. Benoy
M. B. Benoy*
Affiliation:
Mechanics of Solids Group, Engineering Sciences Data Unit, Royal Aeronautical Society
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Extract

Circumstances can arise in which a rectangular panel, forming part of a structure, is subject to non-uniform in-plane compression, and in which it is important that instability of the panel should not occur. Problems of this nature occur, for example, in the structure of modern highspeed aircraft subject to the transient thermal stresses that can arise from rapid changes of speed or altitude.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 73 , Issue 707 , November 1969 , pp. 974 - 977
Copyright
Copyright © Royal Aeronautical Society 1969 

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References

1. Timoshenko, S. and Gere, J. M. Theory of Elastic Stability. Chapter 9, p 348. McGraw-Hill Book Co, London, 1961.Google Scholar
2. Dawe, D. J. Application of the Discrete Element Method to the Buckling Analysis of Rectangular Plates Under Arbitrary Membrane Loading. RAE Tech Rep 68037.Google Scholar
3. The Buckling of Flat Plates in Compression. Structures Data Sheet 02.01.01. Royal Aeronautical Society 1961.Google Scholar
4. Van Der Neut, A. Buckling Caused by Thermal Stresses AGARDograph No 28, High Temperature Effects in Aircraft Structures, pp 215–247. Pergamon Press, London, 1958.Google Scholar