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The Design of Compression Structures for Minimum Weight

Published online by Cambridge University Press:  28 July 2016

D. J. Farrar
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Extract

The primary structure of an aeroplane usually consists basically of a set of tubular beams. The main structural box of the wing or tailplane is a well-known example: a semi-monocoque fuselage is another. For any given loading condition of the aircraft the material in the tube is stressed mainly in tension, in shear, or in compression, depending on its location in the tube cross section.

The aim of the designer is to make the material fulfil these three functions in the most economical manner. In tension, he is limited only by the quality of material available. In shear, this is again substantially the case, although it is well known that very light shear webs over great depths do not develop as high an effective failing stress as do more sturdy webs. This property of dependence on the intensity of loading is much more marked in the case of the compression structure, which is liable to instability in various ways.

Type
Research Article
Information
The Aeronautical Journal , Volume 53 , Issue 467 , November 1949 , pp. 1041 - 1052
Copyright
Copyright © Royal Aeronautical Society 1949

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References

1. Zahorski, Adam. Effects of Material Distributions on Strength of Panels. JOURNAL of Aeronautical Sciences, July 1944.Google Scholar
2. Farrar, D. J. The Failing Stress of Flat Panels with Z-Section Stringers. The Bristol Aeroplane Co. Ltd., Technical Office Report No. 23, Sept. 1945. Scientific and Technical Memorandum No. 19/47.Google Scholar
3. Argyris, J. H. The Initial Instability Stress of Flat Panels with Z-Section Stringers. R.Ae.S. Structures Data Sheet 02.01.25.Google Scholar
4. Farrar, D. J. 1st Addendum, On the Design of Skin-Stringer-Rib Combinations for Compression Surfaces. Addendum to The Bristol Aeroplane Co. Ltd. Technical Office Report No. 39, August 1947.Google Scholar
5. Cox, H. L. Instability of Stringers and Sheet-Stringer Combinations. A.R.C. Report No. Struct. 773.Google Scholar
6. Pugsley, A. G. The Relative Strength and Stiffness Properties Required for Struct Materials. A.R.C. Report No. Struct. 1113.Google Scholar
7. Farrar, D. J. On the Design of Skin-Stringer-Rib Combinations for Compression Surfaces. The Bristol Aeroplane Co. Ltd. Technical Office Report No. 39, April 1947 Google Scholar