Damage modelling of laminated carbon/epoxy composites under static and fatigue loadings |
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| Affiliation: | 1. College of Energy & Power Engineering, Nanjing University of Aeronautics and Astronautics, Jiangsu 210016, PR China;2. Aero-engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Jiangsu 210016, PR China;3. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Jiangsu 210016, PR China;1. School of Mechanical Engineering, Xinjiang University, Urumqi 830046, China;2. Post-Doctoral Research Station of Electrical Engineering, Xinjiang University, Urumqi 830046, China;1. Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Duca degli Abruzzi-24, Torino, Italy;2. Group Material Lab., Centro Ricerche Fiat, strada Torino 50, 10043 Orbassano (TO), Italy;1. School of Mechanical Engineering, Jiangsu University, Zhenjiang, China;2. Department of Mechanical Engineering, The University of Sheffield, Sheffield, United Kingdom;3. Institute for Research and Development, Duy Tan University, Da Nang City, Viet Nam;4. Department of Civil and Environmental Engineering, Tokyo Institute of Technology, Tokyo, Japan;1. School of Mechanical Engineering, Iran University of Science and Technology, Narmak, Tehran 1684613114, Iran;1. Ecole Nationale d’Ingénieurs de Sousse, LMS, Pôle technologique, Route de Ceinture, 4054 Sousse Tunisia;2. Institut Clément Ader ICA, CNRS UMR 5312, 3, Rue Caroline Aigle, 31400 Toulouse, France;3. Arts et Metiers Institute of Technology, CNAM, PIMM, HESAM University, F-75013 Paris, France;4. Zero Emission, FAURECIA CLEAN MOBILITY, 25550 Bavans, France |
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| Abstract: | This study deals with the modelling of the behaviour of laminated carbon/epoxy composites under static and fatigue loading. The non-linear cumulative damage model developed is written on the scale of the plies. It is based on a multi-criterion approach: brittle behaviour in the fibre direction, elastoplastic damage behaviour under shear and transverse tension stress, and elastoplastic behaviour under transverse compression loading. The range of validity of the model described here is limited to the first intra-laminar macro-crack, and it does not account for the delamination processes. This first-ply failure criteria model provides a conservative approach, which should be useful in some industrial context where the highest safety is required. Static tests results obtained on plate samples are presented [±45°]3s and hybrid glass/carbon [0,90]s are presented: they justify the modelling adopted here. The first tension/tension fatigue test results obtained on plate samples [±45°]3s are presented: they are used to identify the parameters of the model contributing to the shear behaviour. |
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