An aerofoil structure for an aircraft, the aerofoil structure comprising a spanwise–extending load-carrying member 10 which is configured to react more than half of all flight loads experienced by the aerofoil structure during flight. The load carrying member is configured to have selected stiffness properties selected such that the aerofoil structure bends and twists in a predefined manner in response to applied flight loads. The aerofoil structure has a leading edge structure 11, a trailing edge structure 12, and upper cover 13 and a lower cover 14 each mounted to the load carrying member. Also provided is a method of manufacturing an aircraft aerofoil structure as previously set out. Also provided is a method of adjusting the bending and twisting behaviour of an aircraft aerofoil structure as previously set out, wherein the method comprises removing the lower cover, altering the stiffness properties of the load-carrying member and replacing the lower cover. The load carrying member may be unitary. A parameter relating to a cross-sectional shape of the load carrying member may vary along the span of the load-carrying member.
Aerofoil structures
2022-10-26
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |