Composite material selection for aircraft structures based on experimental and numerical evaluation of mechanical properties
Апстракт
In this paper determination of mechanical properties of composite material using experimental and numerical approach is presented. The mechanical properties of a laminate obtained in the experiment are used for verification of numerically obtained values, as well as estimation of the load-carrying capacities of composite engine cover of light aircraft. Composite specimens, consisting of epoxy matrix and glass fibers with orientation angles 0 degrees, 45 degrees, and 90 degrees, have been made according to standards, and the mechanical properties were investigated in tensile and three-point bending tests. The tensile strength, bending strength, elasticity modulus, strain, and force at laminate failure have been evaluated and then compared to values obtained in numerical simulations with the aim of verifying the FE model used for failure prediction of structural laminates. Good agreement of experimental and numerical values provides a solid foundation for further improvements of the nume...rical model.
Кључне речи:
Multilayered laminate / Mechanical properties / Fiber orientation angle / CompositeИзвор:
Procedia Structural Integrity - 4th Int Conf Struct Integrity & Durability (ICSID 2020), 2021, 31, 127-133Издавач:
- Elsevier Science Bv, Amsterdam
Финансирање / пројекти:
- Ministry of Education, Science and Technological Development of the Republic of Serbia
DOI: 10.1016/j.prostr.2021.03.021
ISSN: 2452-3216
WoS: 000681323700022
Scopus: 2-s2.0-85119994908
Институција/група
Inovacioni centarTY - CONF AU - Kastratović, Gordana AU - Grbović, Aleksandar AU - Sedmak, Aleksandar AU - Bozić, Z. AU - Sedmak, Simon PY - 2021 UR - https://machinery.mas.bg.ac.rs/handle/123456789/3598 AB - In this paper determination of mechanical properties of composite material using experimental and numerical approach is presented. The mechanical properties of a laminate obtained in the experiment are used for verification of numerically obtained values, as well as estimation of the load-carrying capacities of composite engine cover of light aircraft. Composite specimens, consisting of epoxy matrix and glass fibers with orientation angles 0 degrees, 45 degrees, and 90 degrees, have been made according to standards, and the mechanical properties were investigated in tensile and three-point bending tests. The tensile strength, bending strength, elasticity modulus, strain, and force at laminate failure have been evaluated and then compared to values obtained in numerical simulations with the aim of verifying the FE model used for failure prediction of structural laminates. Good agreement of experimental and numerical values provides a solid foundation for further improvements of the numerical model. PB - Elsevier Science Bv, Amsterdam C3 - Procedia Structural Integrity - 4th Int Conf Struct Integrity & Durability (ICSID 2020) T1 - Composite material selection for aircraft structures based on experimental and numerical evaluation of mechanical properties EP - 133 SP - 127 VL - 31 DO - 10.1016/j.prostr.2021.03.021 ER -
@conference{ author = "Kastratović, Gordana and Grbović, Aleksandar and Sedmak, Aleksandar and Bozić, Z. and Sedmak, Simon", year = "2021", abstract = "In this paper determination of mechanical properties of composite material using experimental and numerical approach is presented. The mechanical properties of a laminate obtained in the experiment are used for verification of numerically obtained values, as well as estimation of the load-carrying capacities of composite engine cover of light aircraft. Composite specimens, consisting of epoxy matrix and glass fibers with orientation angles 0 degrees, 45 degrees, and 90 degrees, have been made according to standards, and the mechanical properties were investigated in tensile and three-point bending tests. The tensile strength, bending strength, elasticity modulus, strain, and force at laminate failure have been evaluated and then compared to values obtained in numerical simulations with the aim of verifying the FE model used for failure prediction of structural laminates. Good agreement of experimental and numerical values provides a solid foundation for further improvements of the numerical model.", publisher = "Elsevier Science Bv, Amsterdam", journal = "Procedia Structural Integrity - 4th Int Conf Struct Integrity & Durability (ICSID 2020)", title = "Composite material selection for aircraft structures based on experimental and numerical evaluation of mechanical properties", pages = "133-127", volume = "31", doi = "10.1016/j.prostr.2021.03.021" }
Kastratović, G., Grbović, A., Sedmak, A., Bozić, Z.,& Sedmak, S.. (2021). Composite material selection for aircraft structures based on experimental and numerical evaluation of mechanical properties. in Procedia Structural Integrity - 4th Int Conf Struct Integrity & Durability (ICSID 2020) Elsevier Science Bv, Amsterdam., 31, 127-133. https://doi.org/10.1016/j.prostr.2021.03.021
Kastratović G, Grbović A, Sedmak A, Bozić Z, Sedmak S. Composite material selection for aircraft structures based on experimental and numerical evaluation of mechanical properties. in Procedia Structural Integrity - 4th Int Conf Struct Integrity & Durability (ICSID 2020). 2021;31:127-133. doi:10.1016/j.prostr.2021.03.021 .
Kastratović, Gordana, Grbović, Aleksandar, Sedmak, Aleksandar, Bozić, Z., Sedmak, Simon, "Composite material selection for aircraft structures based on experimental and numerical evaluation of mechanical properties" in Procedia Structural Integrity - 4th Int Conf Struct Integrity & Durability (ICSID 2020), 31 (2021):127-133, https://doi.org/10.1016/j.prostr.2021.03.021 . .