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Coupled Modes in the Buckling of Panels with Z-Section Stringers in Compression

Published online by Cambridge University Press:  04 July 2016

A. Rothwell
A. Rothwell*
Affiliation:
Department of Aircraft Design, The College of Aeronautics, Cranfield
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Summary

A method of analysis is presented for the interaction between the local and torsional modes of instability of a stiffened panel in compression. Numerical results are produced for the particular case of a panel with Z-section stringers, and the influence of the flange width on the buckling stress is illustrated.

Type
Technical notes
Information
The Aeronautical Journal , Volume 72 , Issue 686 , February 1968 , pp. 159 - 163
Copyright
Copyright © Royal Aeronautical Society 1968 

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References

1. The Royal Aeronautical Society. Structures Data Sheets, Vol II, 02.01.28 Series.Google Scholar
2. Cox, H. L. Computation of Initial Buckling Stress for Sheet-Stiffener Combinations. Journal of the Royal Aeronautical Society, Vol 58, p 634, September 1954.Google Scholar
3. Cox, H. L. The Application of the Theory of Stability in Structural Design. Journal of the Royal Aeronautical Society,Vol 62, p 497, July 1958.Google Scholar
4. Jack, P. W. Initial Buckling of Stiffened Panels in Compression. (Thesis submitted for DCAe, The College of Aeronautics, 1966.)Google Scholar