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Descripción
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| New optimized aerospace structures use composite materials for critical components and subsystems which make essential the knowledge of their fatigue properties. In the present work, the conventional methodology based on linear damage accumulation rules, applied to determine the fatigue life of structures subjected to spectral loads was evaluated for an aeronautical Carbon Fiber Reinforced Epoxy composite material. A test program has been performed to obtain the classical S-N curves at different stress ratios. Constant life diagrams, CLDs, where determined by means of Artificial Neural Networks due to the absence of consistent models for composites. A series of coupons have been tested until failure with a modified version of the standard FALSTAFF load sequence and were compared to the theoretical damage index calculated based on the conventional linear damage accumulation rule. The obtained results show non-conservative predictions. | |
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Internacional
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Si |
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JCR del ISI
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No |
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Título de la revista
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Advanced Materials Research |
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ISSN
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ISSN 1022-6680 |
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Factor de impacto JCR
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Información de impacto
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Volumen
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1016 |
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DOI
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10.4028/www.scientific.net/AMR.1016.8 |
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Número de revista
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Desde la página
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8 |
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Hasta la página
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13 |
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Mes
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AGOSTO |
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Ranking
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