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.