Characterization of the translaminar fracture Cohesive Law |
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| Affiliation: | 1. Department of Applied Mechanics, IIT Madras, Chennai 600036, India;2. Department of Aerospace Engineering, IIT Madras, Chennai 600036, India;1. School of Mechanical and Aerospace Engineering, Queen’s University Belfast, Belfast BT9 5AH, UK;2. DEMec, Faculdade de Engenharia, Universidade do Porto, Rua Dr. Roberto Frias, 4200-465 Porto, Portugal;3. INEGI, Rua Dr. Roberto Frias, 400, 4200-465 Porto, Portugal;4. DICAM, Università degli Studi di Palermo, Viale delle Scienze, 90128 Palermo, Italy;5. DIID, Università degli Studi di Palermo, Viale delle Scienze, 90128 Palermo, Italy;6. Faculty of Civil Engineering and Geosciences, Section of Structural Mechanics, Delft University of Technology, P.O. Box 5048, 2600 GA Delft, The Netherlands;1. Grupo de Elasticidad y Resistencia de Materiales, Escuela Técnica Superior de Ingeniería, Universidad de Sevilla Camino de los Descubrimienos s/n, 41092, Sevilla, Spain;2. Department of Mechanical Engineering, Industrial Doctorate Centre in Machining Science, Computer-Aided Aerospace & Mechanical Engineering (CA2M) Research Group, The University of Sheffield, Sir Frederick Mappin Building, Mappin Street, S1 3JD Sheffield, United Kingdom |
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| Abstract: | Quasi-brittle materials such as fibre-reinforced composite materials develop a relatively large Fracture Process Zone where material toughening mechanisms such as matrix cracking, fibre-bridging and fibre pull-outs take place. The damage onset and damage propagation are well defined from a cohesive model point of view, although no standard procedure has been yet developed to characterize the translaminar Cohesive Law. The present work proposes an objective inverse method for obtaining the Cohesive Law with the use of an analytic model capable of predicting the load–displacement curve of a Compact Tension specimen for any arbitrary Cohesive Law shape. The softening law has been obtained for two laminates, providing an excellent agreement with the experimental results. With the obtained softening function, the nominal strengths of a Center Cracked Specimen and an Open Hole specimen have been predicted for a wide range of specimen sizes. |
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| Keywords: | A. Laminates B. Fracture toughness D. Failure D. Mechanical testing |
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