Hostname: page-component-84b7d79bbc-tsvsl Total loading time: 0 Render date: 2024-07-25T13:54:41.744Z Has data issue: false hasContentIssue false
  • English
  • Français

A Method for Determining the “Safe” Life of an Aircraft Wing From Fatigue Test Results

Published online by Cambridge University Press:  28 July 2016

A. P. Kennedy
A. P. Kennedy*
Affiliation:
Air Registration Board
Get access Rights & Permissions [Opens in a new window]

Extract

It is now the usual practice in Great Britain to estimate the “ safe ” life of an aircraft wing from fatigue tests which are carried out on specimens representing the more highly stressed portions of the tension boom or booms. Such tests are designed to produce a tensile load in the boom equal to that produced in steady flight, and superimposed on this, a small fluctuating load corresponding to that which would be produced by an up gust immediately followed by a down gust of the same magnitude.

Type
Research Article
Information
The Aeronautical Journal , Volume 58 , Issue 521 , May 1954 , pp. 361 - 366
Copyright
Copyright © Royal Aeronautical Society 1954

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Williams, Keri (1952). Fatigue Life of Wing Components for Civil Aircraft. Journal of the Royal Aeronautical Society, November 1952.CrossRefGoogle Scholar
2. Epremian, E., and Mehl, R. F. (1952). Investigations of Statistical Nature of Fatigue Properties. N.A.C.A. Tech. Note 2719, 1952.Google Scholar
3. Sinclair, G. M. and Dolan, T. J. (1953). Effect of Stress Amplitude on Statistical Variability in Fatigue Life of 75ST6 Aluminum Alloy. American Society of Mechanical Engineers, July 1953.Google Scholar
4. Hald, A. (1952). Statistical Theory with Engineering Applications. Chapman & Hall, London, 1952.Google Scholar