Samenvatting

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.