Consecutive matrix cracking in contiguous plies of composite laminates |
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| Institution: | 1. Advanced Composite Evaluation Technology Center, Institute of Space Technology and Aeronautics, Japan Aerospace Exploration Agency, 6-13-1 Osawa, Mitaka, Tokyo 181-0015, Japan;2. Department of Aeronautics and Astronautics, University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8656, Japan;1. University of South Brittany, LIMATB, Rue de Saint Maudé, 56000 Lorient, France;2. Coriolis Composites SAS, Rue Condorcet, Z.A. du Mourillon, 56350 Quéven, France;3. Ifremer, Centre Bretagne, Technopôle Brest Iroise, 29280 Plouzané, France;1. Aerospace Manufacturing Research Centre (AMRC), Faculty of Engineering, Universiti Putra Malaysia, Serdang, Malaysia;2. Laboratory of Biocomposite Technology (BIOCOMPOSITE), Institute of Tropical Forestry and Forest Products (INTROP), Universiti Putra Malaysia, Serdang, Malaysia;3. Department of Aerospace Engineering, Universiti Putra Malaysia, Serdang, Malaysia;1. Jiangsu Key Laboratory of Advanced Structural Materials and Application Technology, Nanjing Institute of Technology, Nanjing 211167, China;2. College of Material Science & Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 211100, China;1. State Key Laboratory of Advanced Technology for Materials Synthesis and Processing, Wuhan University of Technology, 122 Luoshi Road, Wuhan 430070, Hubei, China;2. Lehrstuhl für Carbon Composites, Technische Universitaet Muenchen (TUM), Germany;3. Department of Mechanical Engineering, University of Bristol, Bristol BS8 1TR, UK;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 |
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| Abstract: | Propagation behaviors of obliquely-crossed microcracks induced by matrix cracks in adjacent plies of composite laminates were numerically analyzed using finite element modeling. Oblique coordinate system along obliquely-crossed cracks was defined and applied to the finite element formulation, which enabled geometrically parametric analysis for arbitrary oblique angles using a single discrete model. Three-dimensional stress analyses of S/θn/90]s laminate with microcracks in θ-ply and fully developed matrix cracks in 90-ply were performed under various conditions of angle θ, θ-ply crack length, θ-ply thickness, etc. Energy release rates associated with θ-ply crack propagation in the θ-ply fiber direction were calculated in order to assess θ-ply cracking conformations. The results suggested that presence of 90-ply cracks affects θ-ply crack propagation, especially mode-I energy release rates, depending on angle θ. Furthermore, effects of angle θ, θ-ply thickness and S layer configuration on the interaction between matrix cracks in θ- and 90-plies were clarified. Finally, crack accumulation behaviors in 0/θ2/90]s laminates were experimentally investigated and compared with the analytical results. |
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