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Measurement of the fracture toughness associated with the longitudinal fibre compressive failure mode of laminated composites
Authors:MJ Laffan  ST Pinho  P Robinson  L Iannucci  AJ McMillan
Affiliation:1. Department of Aeronautics, Imperial College London, London SW7 2AZ, UK;2. Rolls-Royce plc, PO Box 31, Derby DE24 8BJ, UK;3. Royal Society Industrial Fellow, ACCIS, University of Bristol, 83 Woodland Road, Bristol BS8 1US, UK;1. DEMec, Faculdade de Engenharia, Universidade do Porto, Rua Dr. Roberto Frias, s/n, 4200-465 Porto, Portugal;2. INEGI, Instituto de Ciência e Inovação em Engenharia Mecânica e Engenharia Industrial, Rua Dr. Roberto Frias, 400, 4200-465 Porto, Portugal;3. CITAB, Universidade de Trás-os-Montes e Alto Douro, Engenharias I, Apartado 1013, 5001-801 Vila Real, Portugal;1. Institute of Structural Analysis, Leibniz Universität Hannover, Germany;2. LMT-Cachan (ENS Cachan/CNRS/Université Paris-Saclay), F-94230 Cachan, France;1. Material Technologies, Swerea SICOMP, Argongatan 30, 431 53 Gothenburg, Sweden;2. Aeronautics Department, Imperial College London, South Kensington Campus, SW7 2AZ London, UK;3. GKN Aerospace CTC, The National Composites Centre, BS16 7FS Bristol, UK;4. Physical Sciences Department, DSTL, 415 BLDG, Porton Down, SP4 0JQ Wiltshire, UK;1. Singapore Institute of Manufacturing Technology, Singapore 637662, Singapore;2. Composites Centre, Imperial College London, South Kensington, London SW7 2AZ, United Kingdom;3. Chalmers University of Technology, 412 96 Göteborg, Sweden;1. INSA Rouen, Groupe de Physique des Matériaux (UMR CNRS 6634), 76801, St Etienne du Rouvray, France;2. Institut Clément Ader (UMR CNRS 5312), Université de Toulouse, ISAE-SUPAERO, 10 av. E. Belin, 31055, Toulouse cedex 4, France
Abstract:The fracture toughness associated with the fibre compressive failure was obtained from testing notched unidirectional carbon/epoxy four-point-bend specimens. Microscopy of failed specimens revealed that onset of damage was characterised by the formation of a single line of fibre breaks at approximately 45° to the plane of the initial notch. A micromechanical finite element model was used to investigate this failure scenario and it was concluded that the most probable cause of the damage morphology was compression-induced shear failure of the composite. An intrinsic material property in this case was deemed to be the mode II critical strain energy release rate associated with the initiation of the 45° crack. For IM7/8552, this was measured to be GIIc = 4.5 ± 0.8 kJ/m2.
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