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Strength of Aeroplanes in Relation to Repeated Loads*

Published online by Cambridge University Press:  07 June 2016

D. Williams
D. Williams*
Affiliation:
Structures Department, Royal Aircraft Establishment
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Summary

The present position relating to the effect of repeated loads on aircraft structures is reviewed from the point of view of the capacity of aircraft structures to withstand such loads and also of their frequencies of occurrence in the life of the aircraft.

A rough account is given of the statistical methods by which such frequencies can be estimated, and the conclusions to which the use of these methods leads are discussed.

The note ends with an outline of a suggested programme of research and a brief statement of the conclusions reached.

Type
Research Article
Information
Aeronautical Quarterly , Volume 1 , Issue 4 , February 1950 , pp. 291 - 304
Copyright
Copyright © Royal Aeronautical Society. 1950

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Footnotes

*

Modified Paper (A.R.C. No. 9965) received December 1948.

References

1. Oaks, J. K., and Townshend, P. H. (1945). Fluctuating Load Tests on Typhoon Tailplanes. R.A.E. Report No. S.M.E. 3354, December 1945.Google Scholar
2. Hartmann, E. C. (1941). Fatigue Test Results—Their Use in Design Calculations. Research Laboratories, Aluminum Company of America. Product Engineering, Feb. 1941.Google Scholar
3. Montagnon, P. E., and Day, A. (1945). The Choice of Loads for Ultimate and Repeated Design and Test Conditions. R.A.E. Tech. Note No. S.M.E. 325, June 1945.Google Scholar
4. Starkey, R. D., and Cox, D. R. (1945). The Connection Between the Strength and Load Frequency Distributions for the Lancaster and the Structural Accident Rate. R.A.E. Tech. Note No. S.M.E. 335, October 1945.Google Scholar
5. Walker, P. B. (1949). The Fatigue of Aircraft Structures. Journal of The Royal Aeronautical Society, Vol. 53, No. 464, August 1949.CrossRefGoogle Scholar