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The Optimum Design of Compression Surfaces having Unflanged Integral Stiffeners

Published online by Cambridge University Press:  28 July 2016

E. J. Catchpole
E. J. Catchpole*
Affiliation:
Vickers-Armstrongs Ltd., Weybridge
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Summary

A method is developed enabling rapid determination of the optimum cross-sectional dimensions of compression surfaces having unflanged integral stiffeners, and consideration is given to the effects of practical limitations on the design. The theoretical efficiency of the optimum integral design is found to be only 85 per cent, of that of optimum Z-stringer design.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 58 , Issue 527 , November 1954, pp. 765 - 768
Copyright
Copyright © Royal Aeronautical Society 1954

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References

1. Keen,, E. D. (1953). Integral Construction—Its Application to Aircraft Design and its Effect on Production Methods. Journal of the Royal Aeronautical Society, April 1953.Google Scholar
2. Legg,, K. L. C. (1954). Integral Construction—A Survey, and an Experiment. Journal of the Royal Aeronautical Society, July 1954.Google Scholar
3. Farrar,, D. J. (1949). The Design of Compression Structures for Minimum Weight. Journal of the Royal Aeronautical Society, November 1949.CrossRefGoogle Scholar
4. Royal Aeronautical Society's Structures Data Sheets 02.01.28 to 37. Buckling Stress of Sheet-Stringer Combinations in Compression. (To be issued, with others, by the end of this year.—Editor.)Google Scholar
5. Van Der Neut,, A. (1952). The Local Instability of Compression Members, Built up from Flat Plates. Technische Hogeschool Vliegtuigbouwkunde, Report VTH-47, 1952.Google Scholar
6. Royal Aeronautical Society's Structures Data Sheet 02.01.25.Google Scholar
7. Royal Aeronautical Society's Structures Data Sheets 00.02.01 to 03.Google Scholar
8. Cox,, H. L. (1954). Computation of Initial Buckling Stress for Sheet-Stiffener Combinations. Journal of the Royal Aeronautical Society, September 1954.Google Scholar