The aerofoil shaped body, forming part of an aircraft wing (fig.1,3) has longitudinal spars 11,21 and upper and lower aerofoil covers 22,12 formed from a composite laminate material; at least one of the spars 11,21 is integrally formed with one of the covers such that the laminate material extends continuously from the spar into the cover through a curved fold region 14,24 extending along a longitudinal fold axis 15,25 which when projected onto two orthogonal planes has curvature in both. Each spar 11,21 may each be integrated with one of the two covers 12,22, forming two variable thickness L-shaped spar-covers with a fold angle between 60 to 120 degrees; alternatively an attachment flange 13,23 may be provided forming Z-shaped spar-covers. Preferably the fold region has a rounded corner (fig.9,r) with variable radius along the fold axis. Preferably there are attachment brackets for leading or trailing edge structures (fig.2,30,40) and the aerofoil shaped body may form a winglet. Preferably the wing of the aircraft passes over the fuselage and has downlets (fig.12,207) formed in the upper and lower covers. A method of manufacture of the composite laminate bodies is also claimed.
Aerofoil body with integral curved spar-cover
2017-11-22
Patent
Electronic Resource
English