An aircraft assembly comprises a longitudinal spar 14 and an aerofoil cover 12 integrally formed from a composite laminate material to form a unitary spar-cover such that the spar extends continuously into the cover through a fold region 17, where the spar and cover are separated by a recess 30 at a longitudinal end of the fold region, to define a spar end region and a cover end region, and a reinforcement element 35, which may comprise a metal bridging element extends between the spar end region and the cover end region to couple the spar end region with the cover end region.
Aircraft assembly having an integral spar-cover
2020-12-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |