Abstract
A numerical algorithm of fatigue crack growth prediction on aircraft fuselage panels with multiple site damage is discussed in this paper based on Finite Element Method. The objective of this research is to realize the automatic crack propagation and crack growth life calculation. The mixed-mode stress state of structures at crack tip is considered through the published form of effective stress intensity factor, and the incremental fatigue crack growth model is studied to coordinate the propagation between multiple cracks. Maximum tangential stress criterion is applied to determine the crack growth direction at a growth step. Moreover, the new crack tip position in flat plates and curved plates are numerically determined to automatically update the crack tip. Fatigue test of curved panel subjected to inner pressure was conducted by horizontal self-balanced test facility, and the fatigue tests of plates with two internal collinear cracks or with seven collinear cracks under tensile stress were also analyzed to validate the feasibility of algorithm. It is shown that the efficient fatigue crack prediction algorithm is able to predict various crack growth behaviors observed in tests, and the predicted crack propagation path and lives are in a good agreement with test results and data available in the literature.
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Su, S., Liao, J., Zhang, W., Dong, D. (2020). Fatigue Crack Growth Prediction and Verification of Aircraft Fuselage Panels with Multiple Site Damage. In: Niepokolczycki, A., Komorowski, J. (eds) ICAF 2019 – Structural Integrity in the Age of Additive Manufacturing. ICAF 2019. Lecture Notes in Mechanical Engineering. Springer, Cham. https://doi.org/10.1007/978-3-030-21503-3_32
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DOI: https://doi.org/10.1007/978-3-030-21503-3_32
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