Publicação: Residual modulus degradation model for woven fabric composite determined by impulse excitation technique
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Structural components in the aircraft industries often require geometries that induce stress concentration effects, intensifying fatigue phenomena. When combined with a lack of structural monitoring it may limit composite applications. This research focuses on stiffness reduction of a notched carbon fiber laminate subjected to tension-tension fatigue load. The stiffness reduction was monitored during the cyclic tests by the use of the impulse excitation technique. Three major degradation stages were observed, the initial stage showed a high degradation rate followed by constant modulus degradation. The last stage was related to the presence of extensive delamination occurring outside of the notch area.
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5HS woven, Carbon fiber, Crack propagation, Delamination, Epoxy
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Inglês
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International Journal of Fatigue, v. 133.
