Abstract
Fiber metal laminates (FMLs) are hybrid materials developed in recent years, mainly for aeronautical applications. These applications require specific mechanical properties like fatigue resistance and high strength-weight ratios. However, in-depth analyses and measurement techniques for fracture toughness have not been widely published. This work presents a proposal to characterize the fracture toughness of a laminate comprised by layers of carbon-epoxy woven and 20-24T3 Aluminum. First, an approach to consider laminate specimens as linear-stiffness elements in parallel for 3 PB loading is presented. This allows to estimate the force received by each material from the total force applied to the specimen. Next, the Strain Intensity Factor is introduced to characterize the crack tip stress for isotropic and especially orthotropic materials under plane stress. A Finite Element Analysis (FEA) is used to verify the proposed models. The effect of considering a perfect bond between the two materials is detailed. Finally, experimental activities to measure the fracture toughness are described. The approaches and FEA previously referred are put in practice. The results are presented and discussed. The conclusion of this work emphasizes the usefulness of the stiffness approach and the convenience of the Strain Intensity Factor as a common measure of the fracture toughness of the laminate materials, in static and dynamic regimes.
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Figueroa, J.G.M., Llanas, P.I.A. (2018). Fracture Toughness of Fiber Metal Laminates Through the Concepts of Stiffness and Strain-Intensity-Factor. In: Ambriz, R., Jaramillo, D., Plascencia, G., Nait Abdelaziz, M. (eds) Proceedings of the 17th International Conference on New Trends in Fatigue and Fracture. NT2F 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-70365-7_37
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DOI: https://doi.org/10.1007/978-3-319-70365-7_37
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