Patent ID: 9381992
Filing Date: 2016-07-05
CPC Classification: B64C

Claim Text:
1. A leading edge for an aircraft lifting surface, comprising: an inboard leading edge section and an outboard leading edge section arranged span-wise so as to form together the aerodynamic surface of the leading edge, and each of said outboard and inboard leading edge sections comprising a skin panel comprising a substantially C-shaped cross-sectional configuration and a support structure internally joined to the skin panel, wherein said support structure comprises a number of spars longitudinally arranged along the leading edge, wherein the support structure of the outboard leading edge section has less spars than the inboard leading edge section, wherein the support structure of the inboard leading edge section comprises: a main spar, a front spar and an intermediate spar, wherein the front and intermediate spars are shorter than the main spar, and wherein the main, front and intermediate spars are obliquely arranged, in such a manner that the front and intermediate spars are inclined in an opposite direction to the inclination of the main spar.