The use of composites materials for aircraft design allows integrating other different materials with non-structural functions thanks to the layered structure. This layered structure offers the opportunity to embed damping interleaves in the CFRP laminate to improve the vibroacoustic damping behaviour of the structure. These multifunctional structures will result in hybrid configurations which combine traditional CFRP laminate with other materials such as rubbers or nanoparticles.

Therefore, hybrid configurations need to be developed and compared with current structural solutions to quantify their improvement in terms of weight savings or functionality improvement. This proposal planned to manufacture curved (hybrid skin) panels stiffened with twisted stringers of different shape section by co-curing in female curing tool in one-shot process. Curved panels manufactured were representative of the structure that conforms the nose fuselage stiffened skin.