Fractographic relation between progressive failure and strain measurement techniques for recently developed configuration of carbon fiber/epoxy laminate |
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| Institution: | 1. Tecnológico Nacional de México/Centro Nacional de Investigación y Desarrollo Tecnológico (CENIDET), Prolongación Palmira s/n esq, Apatzingán, Col. Palmira, Cuernavaca, Morelos, Mexico;2. CIICAp/FCQeI/Universidad Autónoma del Estado de Morelos Av, Universidad 1001 Col, Chamilpa C.P, 62209 Cuernavaca, Morelos, Mexico;3. Facultad de Química/ICF/Universidad Nacional Autónoma de México, Coyoacán, D. F. C. P. 04510, Mexico;1. Department of Astronautical Science and Mechanics, Harbin Institute of Technology, Harbin 150001, People''s Republic of China;2. Center of Composite Materials and Structures, Harbin Institute of Technology, Harbin 150080, People''s Republic of China;1. Instituto de Investigaciones en Ciencia y Tecnología de Materiales, Universidad Nacional de Mar del Plata–Consejo Nacional de Investigaciones Científicas y Técnicas, Av. J. B. Justo 4302, 7600, Mar del Plata, Argentina;2. Acoustics and Lighting Laboratory, Scientific Research Commission of Buenos Aires Province, Centenario y 506, Gonnet, Buenos Aires, Argentina;1. Polymer Processing and Flow (P-PROF) Group, School of Energy, Environment and Materials, King Mongkut''s University of Technology Thonburi (KMUTT), 126 Pracha Uthit Rd., Bang Mod, Thung Khru, Bangkok, 10140, Thailand;2. Department of Materials Engineering, Faculty of Engineering, Kasetsart University, 50 Ngamwongwan Rd., Ladyao, Chatuchak, Bangkok, 10900, Thailand;2. Department of Civil Engineering, Federal University of São Carlos, Brazil;3. Federal Centre for Technological Education of Minas Gerais, Department of Civil Engineering, Brazil;4. Advanced Composites Centre for Innovation and Science, University of Bristol, UK |
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| Abstract: | In this work, fracture mechanisms of a newly developed carbon fiber/epoxy laminate +75/0/-75]s were assessed by scanning electron microscopy (SEM). The composite strain-stress curves were plotted with the displacement information simultaneously acquired from both a tensile testing machine crosshead and an extensometer. The strain-stress curve plotted with the displacement data from the machine test showed an average slope change from E1m = 22.783 GPa to E2m = 13.170 GPa on about 65% of the total strain before global failure, while strain-stress curves plotted with displacement data from the extensometer showed one single slope. While results reported in literature related to composite failure mechanisms, where some authors reported a slope change in strain-stress curves associated to progressive failure, experimental evidence in this work for strain-stress curves showed one single slope, indicating that such slope change is related to the strain measuring technique, and not to a progressive failure. The fracture surface was studied, and four main features were observed, which were related to failure mechanisms during the uniaxial test. The identified failure mechanisms occurred on a stage above 93% of the total strain before global failure. |
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| Keywords: | Carbon fiber/epoxy laminates Composites Fractography Tensile failure SEM |
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