The component 100 for an aerofoil structure is a unitary spar 13 and cover panel 12 with a flat intermediate section 11 connecting them, formed with angles α, β, both in the range 90-180º, between the cover, intermediate section and spar. Preferably the component is made from a composite material to form a torsion box in an aircraft wing; the angles are selected so the plane of the intermediate section 17 intersects a location on a leading or trailing edge structure 15 of the aerofoil at, or near, a location at which an in-flight aerodynamic load 16 is expected to be applied to the aerofoil. Mounting brackets (fig.3a,30) or bars (fig.4a,40) for attaching the edge structures 15,(fig.3a,33),(fig.4a,43) may be fixed to the intermediate section; the brackets may be additionally fixed to the spar and spaced apart (fig.3b) to correspond with edge structure mounting features 34; the bars may have a V-shaped cross-section to house other aircraft system components. Seals (fig.4a,45) may be provided in the gap between the edge structures and the cover. A method of assembling an aerofoil structure is also claimed, where the mounting features may have fastening holes (fig.3a,32) for passing fasteners through.
Aerofoil structure components
2018-06-20
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |