Abstract
In this investigation, fatigue criterion was established to predict crack-initiation at the tip of a notch in aged hardening aluminum alloy. This criterion was used to predict the residual lifetime in aeronautical structures using concept of local stress at notch and subjected to constant amplitude loading characterized by mean stress. Charpy V-notch specimens were taken from sheet plate and the notch radius accurately machined at value of 0.2mm. The local stresses were determined numerical and validated analytically. In experimental investigation, the V-notched specimens were loaded in four point bending fatigue with a load ratio R=0.1 and variation in amplitude loading.
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Article history
- ReceivedUntil the next stage: 69 days
- Revision requestedUntil the next stage: 92 days
- RevisedUntil the next stage: 0 days
- AcceptedUntil the next stage: 13 days
- Published
About the authors
Mustapha Benachour
Professor and Researcher in Materials Sciences and Mechanical Engineering.
Mechanical Engineering Department
Nadjia Benachour
Doctor in materials Sciences and Physic's
Mohamed Benguediab
Professor in materials Sciences, especially in fatigue and fracture mechanics of ferrous and non-ferrous materials and alloys.
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Copyright © 2019 Mustapha Benachour, Nadjia Benachour, Mohamed Benguediab.
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