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Fatigue in Aircraft Design

Published online by Cambridge University Press:  28 July 2016

B. E. Stephenson
B. E. Stephenson*
Affiliation:
Vickers-Armstrongs Ltd.
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Extract

The problem of fatigue in aircraft design is a comparatively new one so far as the airframe designer is concerned. There are three main reasons for its prominence. Firstly, the utilisation rate has increased enormously, particularly with transport types; indeed, the hours flown by a civil aeroplane in a single year nowadays far exceed those in the whole life of a bomber up to the period of the 1939-45 War. Secondly, the increased cruising speeds of modern aircraft have aggravated the loading conditions which give rise to fatigue; and thirdly, the development of modern high strength light alloys has enabled higher ultimate stresses to be used, although the fatigue resistance of the material has not kept pace with its ultimate strength.

Type
A Discussion on Fatigue
Information
The Aeronautical Journal , Volume 57 , Issue 513 , September 1953 , pp. 584 - 588
Copyright
Copyright © Royal Aeronautical Society 1953

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References

1. Walker, P. B. (1953). Design Criterion for Fatigue of Wings. Journal of the Royal Aeronautical Society, January 1953.CrossRefGoogle Scholar
2. Taylor, J. (1953). Measurement of Gust Loads in Aircraft. Journal of the Royal Aeronautical Society, February 1953.CrossRefGoogle Scholar