Abstract
This paper presents the effect of matrix type on creep behavior at 80% loads of ultimate tensile strength of two laminated composites at different fiber and matrix system. For this, two types of laminated composites were manufactured based on two types of fibers (carbon fabric and glass fabric) with different matrix systems EPOCAST 50-A1 (EP50-A), Epoxy STR (STR) and Epoxy INJ812 (INJ). The tensile and creep behavior of each laminated composite was studied in the same test conditions. A microstructural study was also investigated by SEM-microscopy on the morphology of composite specimens after creep rupture failures at 80% of applied load. The obtained results showed clearly the influence of matrix type used on the tensile and creep behavior of studied composites. Indeed, it was noted that no creep rupture failures were observed in short-term (less than 4 h) for INJ/Carbon composite at tensile creep tests at 80% loads of ultimate tensile strength. At the same ultimate tensile strength, EP50/Carbon composite showed a best creep behavior up to 30 h and had a creep modulus higher than other laminated composites. The observation of rupture facets of all composite samples showed clearly that the rupture will take place in the direction of loading, creating voids at the interface resin/fiber. These are observed based on the nature of the matrix used. Key words: Epoxy, aliphatic amine, cross-linked, carbon fabric, glass fabric, creep test, cyclic tensile test.
Highlights
Technological evolution of composite materials in aeronautics sector continues to lead to the development of new designs for technical and economic purposes, which include mechanical performances and cost reduction for best operation of aircrafts (Asundi and Choi, 1997; Soutis, 2005; Botelhoa et al, 2006; Botelho and Rezende, 2000)
This paper presents the effect of matrix type on creep behavior at 80% loads of ultimate tensile strength of two laminated composites at different fiber and matrix system
It should be noted that the presence of microspores in the EP50/Carbon laminate is not important compared to that obtained by STR/Carbon (Goertzen and Kessler, 2006; Yan et al, 2017)
Summary
Technological evolution of composite materials in aeronautics sector continues to lead to the development of new designs for technical and economic purposes, which include mechanical performances and cost reduction for best operation of aircrafts (Asundi and Choi, 1997; Soutis, 2005; Botelhoa et al, 2006; Botelho and Rezende, 2000). It is desired to use composite materials whose specific properties are superior to those of conventional materials (Botelho and Rezende, 2000; Tarpani et al, 2006a, b). The advantage of associating performances with reduced weight of aircraft structural elements was one of the main purposes of aviation composites development. Laminated composites are selected for weight critical applications and have the best behavior as far as fatigue failure is concerned (Tarpani et al, 2006b).
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
