Author(s): Sumalatha B.P, H.V Lakshminarayana , Rudresh M
Published in: International Journal of Engineering Research & Technology
License: This work is licensed under a Creative Commons Attribution 4.0 International License.
Volume/Issue: Vol.1 - Issue 6 (August- 2012)
Fatigue failure analysis plays a significant role in all industrial design applications. Many components are subjected to some form of fluctuating stress/strain, and thus fatigue failure potentially plays a significant role in the assessment of structural integrity. The occurrence of cracks in structures and components poses a real threat to the well-being of the structures. These cracks may grow and result in loss of integrity and at times, total structural failure. Presented in this paper are the results of a research program on damage tolerance analysis and design of aerospace structures. The problem considered is an aircraft fuselage structural panel plate between two repeating rivet holes with a crack originating from one hole and approaching to the other hole is generic problem. The first problem generates accurate Stress Intensity Factor solution for Fatigue crack growth test panel using ANSYS. The second problem provides verification of fatigue crack growth life prediction using AFGROW software. Foreman, Harter, NASGRO and Walker FCG equations are used for prediction of crack growth life under constant amplitude loading.
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