Prediction of Fatigue Crack Growth After Single Overload in an Aluminum Alloy
Author:
Affiliation:
1. National Aerospace Laboratories, Bangalore 560 017, India
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.880
Reference42 articles.
1. Prediction Methods for Fatigue Crack Growth in Aircraft Material
2. A review of crack closure, fatigue crack threshold and related phenomena
3. A new (ΔK+Kmax)0.5 driving force parameter for crack growth in aluminum alloys
4. A fatigue crack driving force parameter with load ratio effects
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