MATEC Web Conf.
Volume 314, 2020International Cross-Industry Safety Conference (ICSC) – International Symposium on Aircraft Technology, MRO and Operations (ISATECH) (ICSC-ISATECH 2019)
|Number of page(s)
|International Symposium on Aircraft Technology, MRO and Operations
|29 May 2020
Finite element modelling of carbon fiber - carbon nanostructure - polymer hybrid composite structures
National and Kapodistrian University of Athens, General Department, Greece
2 Amsterdam University of Applied Sciences, Faculty of Technology, Aviation Academy, Netherlands
* Corresponding author: firstname.lastname@example.org
The present study deals with the numerical modelling of hybrid laminated composites, which can be proved especially useful in the engineering and maintenance of advanced aerospace primary structures. The lamina is comprised of continuous carbon fibers, thermosetting epoxy polymer matrix, as well as carbon nanostructures, such as graphene or carbon nanotubes, inclusions. Halpin-Tsai equations combined with results obtained from nanomechanical analysis are employed in order to evaluate the elastic properties of the carbon nanostructure/polymer matrix. Then, the obtained elastic properties of the hybrid matrix are used to calculate the orthotropic macro-mechanical properties of the unidirectional composite lamina. A hybrid composite plate is modelled as a 2D structure via the utilization of 4-node, quadrilateral, stress/displacement shell finite elements with reduced integration formulation. The convergence and analysis accuracy are tested. The mechanical performance of the hybrid composites is investigated by considering specific configurations and applying appropriate loading and boundary conditions. The results are compared with the corresponding ones found in the open literature, where it is possible.
© The Authors, published by EDP Sciences, 2020
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