Finite element modelling of carbon fiber - carbon nanostructure - polymer hybrid composite structures

The present study deals with the numerical modelling of hybrid<br/>laminated composites, which can be proved especially useful in the<br/>engineering and maintenance of advanced aerospace primary structures. The<br/>lamina is comprised of continuous carbon fibers, thermosetting epoxy<br/>polymer matrix, as well as carbon nanostructures, such as graphene or<br/>carbon nanotubes, inclusions. Halpin-Tsai equations combined with results<br/>obtained from nanomechanical analysis are employed in order to evaluate<br/>the elastic properties of the carbon nanostructure/polymer matrix. Then, the<br/>obtained elastic properties of the hybrid matrix are used to calculate the<br/>orthotropic macro-mechanical properties of the unidirectional composite<br/>lamina. A hybrid composite plate is modelled as a 2D structure via the<br/>utilization of 4-node, quadrilateral, stress/displacement shell finite elements<br/>with reduced integration formulation. The convergence and analysis<br/>accuracy are tested. The mechanical performance of the hybrid composites<br/>is investigated by considering specific configurations and applying<br/>appropriate loading and boundary conditions. The results are compared with<br/>the corresponding ones found in the open literature, where it is possible.