Influence of internally dropped-off plies on the impact damage of asymmetrically tapered laminated CFRP |
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| Affiliation: | 1. Université de Toulouse; INSA, UPS, Mines ALBI, ISAE; ICA (Institut Clément Ader), ISAE (Institut Supérieur de l’Aéronautique et de l’Espace), 10, avenue Edouard Belin, BP 54032-31055 Toulouse Cedex 4, France;2. Sogeti High Tech, Avenue Escadrille Normandie Niemen, Parc du Millénaire, 31703 Blagnac, France;1. School of Metallurgy and Materials Engineering, University of Tehran, Tehran, Iran;2. Center of Excellence for High Performance Materials, University of Tehran, Iran;1. Centre for Advanced Materials Technology (CAMT), School of Aerospace, Mechanical and Mechatronic Engineering, The University of Sydney, NSW 2006, Australia;2. Department of Fiber Science & Apparel Design, College of Human Ecology, Cornell University, Ithaca, NY 14853, USA;1. Department of Aerospace Engineering, Tohoku University, 6-6-01 Aoba-yama, Aoba-ku, Sendai, Miyagi 980-8579, Japan;2. Department of Materials Science and Technology, Tokyo University of Science, 6-3-1 Niijuku, Katsusika-ku, Tokyo 125-0051, Japan;3. Department of Aerospace Engineering, Texas A&M University, 736A H.R. Bright Building, 3141 TAMU, College Station, TX 77843-3141, USA;4. Department of Engineering Sciences and Mathematics, Luleå University of Technology, SE 97187 Luleå, Sweden;1. schlaich bergermann partner sbp gmbh, Schwabstrasse 43, 70197 Stuttgart, Germany;2. Chair of Conceptual and Structural Design, Berlin Institute of Technology, Gustav-Meyer-Allee 25, 13355 Berlin, Germany;3. SGL Carbon GmbH, Werner-von-Siemens-Strasse 18, 86405 Meitingen, Germany |
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| Abstract: | This paper presents an experimental study of low velocity impact response of carbon/epoxy asymmetrically tapered laminates. The tests are realised at energy between 10 and 30 J on two types of layup with multiple terminated plies. The type and localisation of damage are analysed using C-scan and micrographs. Then, the data is compared with the response of corresponding respective plain laminate. The effects of some tapering parameters (taper angle, drop-off disposition and configuration) on the impact damage mechanisms are also investigated. Very similar impact damage phenomena are found between tapered and plain laminates. The presence of material discontinuity due to the resin pocket affects less the damage mechanism than the structural difference between the thick and the thin sections. |
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| Keywords: | A Carbon fibre B Impact behaviour C Damage mechanics Ply drop-off |
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