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Fatigue Tests and Aircraft Life Evaluation: On the Experimental Correlation of Service Endurance Tests with Fatigue Tests at Constant Stress Amplitude

Tibor Haas, Dipl.Ing., A.M.I.Mech.E., A.F.R.Ae.S. (Head of Fatigue Laboratory, Aircraft Division, The Bristol Aeroplane Co. Ltd., Filton.)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 October 1955

Abstract

THE method used at present in fatigue testing aircraft joints and components by applying cycles of constant stress amplitude of a magnitude considered to be the most damaging is based on the assumption that Miner's cumulative damage rule, Σ(n/N)&equals l, holds good. This rule is known to be true only under certain conditions which may not apply to those under which fatigue damage is accumulated in aircraft.

Citation

Haas, T. (1955), "Fatigue Tests and Aircraft Life Evaluation: On the Experimental Correlation of Service Endurance Tests with Fatigue Tests at Constant Stress Amplitude", Aircraft Engineering and Aerospace Technology, Vol. 27 No. 10, pp. 334-338. https://doi.org/10.1108/eb032611

Publisher

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MCB UP Ltd

Copyright © 1955, MCB UP Limited