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A method of calculating the safe fatigue life of compact, highly-stressed componentsThis paper describes a method which has been developed for estimating the safe fatigue life of compact, highly-stressed and inaccessible components for aeroplanes and helicopters of the Royal Air Force. It is explained why the Design Requirements for British Military Aircraft do not favor the use of a damage-tolerance approach in these circumstances.
Document ID
19950008050
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cardick, Arthur W. (Defence Research Agency Farnborough, Hampshire, United Kingdom)
Pike, Vera J. (Defence Research Agency Farnborough, Hampshire, United Kingdom)
Date Acquired
September 6, 2013
Publication Date
September 1, 1994
Publication Information
Publication: NASA. Langley Research Center, FAA(NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance
Subject Category
Structural Mechanics
Accession Number
95N14464
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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