Evaluation of the Fatigue Linear Damage Accumulation Rule for Aeronautical CFRP Using Artificial Neural Networks

Abstract:

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.

• Periodical: Advanced Materials Research (Volume 1016)
• Pages: 8-13
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.1016.8
• Online since: August 2014
• Authors: Pablo Zuluaga-Ramírez*, Malte Frövel, Álvaro Arconada, Tomás Belenguer, Félix Salazar
• Keywords: Artificial Neural Network (ANN), Composite Structures, Fatigue, Palmgren-Miner, Spectrum Loads

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DOI: 10.4028/www.scientific.net/kem.569-570.88

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