Patent ID: 6386481
Filing Date: 2002-05-14
Classification: B64C

Abstract:
An aircraft wing structure comprising an upper skin forming the upper surface of the wing and a lower skin forming the lower surface of the wing, and a wing frame between said skins,whereby the wing frame comprises at least one transverse wing rib and at least one longitudinal upper stringer, to which the upper skin is fastened and correspondingly at least one lower stringer, to which the lower skin is fastened, and also a front spar forming the forward edge of wing frame fastened to the wing rib and correspondingly a rear spar forming the aft edge of the wing frame, wherein the wing rib is an elongated portion comprising a first vertical side surface and correspondingly a second vertical side surface, whereby at least one elongated fastening element extending from the upper part of the side surface to the lower part of the side surface is arranged to at least one side surface of the wing rib, which fastening element comprises a substantially plate-like flexible portion, whose first longitudinal edge is fastened to be immovable to the side surface of the wing rib, and the second longitudinal edge of the flexible portion comprises a stiffening portion, the flexible portion in the fastening element is formed to be bendable in the longitudinal direction of the wing rib, whereby the flexible portion enables to move the stiffening portion a predetermined distance in the longitudinal direction of the wing rib, the first and second ends of the stiffening portion in the fastening element comprises fastening portions, from which the fastening element is fastened to the stringer on the upper surface side of the wing and correspondingly to the stringer on the lower surface side of the wing, and which stiffening portion in the fastening element is arranged to carry vertical loads between said stringers.