A method of manufacturing an aerodynamic structure, for example, an aircraft wing tip, is disclosed. The method includes providing an upper cover having a plurality of lugs, providing a lower cover having a plurality of lugs, measuring the distance between a lug on the upper cover and corresponding lug on the lower cover, selecting, from the plurality of different sized links, a link suitably sized to correspond to the measured distance between the lug on the upper cover and corresponding lug on the lower cover, connecting the selected link to the lug on the upper cover and corresponding lug on the lower cover; and repeating those steps such that each lug on the upper cover is joined to a corresponding lug on the lower cover.

A method of manufacturing an aerodynamic structure, for example, an aircraft wing tip, is disclosed. The method includes providing an upper cover having a plurality of lugs, providing a lower cover having a plurality of lugs, measuring the distance between a lug on the upper cover and corresponding lug on the lower cover, selecting, from the plurality of different sized links, a link suitably sized to correspond to the measured distance between the lug on the upper cover and corresponding lug on the lower cover, connecting the selected link to the lug on the upper cover and corresponding lug on the lower cover; and repeating those steps such that each lug on the upper cover is joined to a corresponding lug on the lower cover.

A method of sealing an aircraft wing vent stringer may include placing a movable sealant sled in a vent stringer cavity of an aircraft wing. The sealant sled may include a sealant source configured to apply sealant to a wing portion within the vent stringer. The sealant sled may be transported through the cavity in a longitudinal direction defined by the wing, thereby applying a layer of sealant to the wing. In some cases, vent stringer may be abraded and/or washed before sealing. In some cases, two or more layers of sealant may be applied, one of which may be a secondary fuel barrier.

An aerodynamic structure incorporated in an aircraft control surface (10) provides a spar (16) extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

An aerodynamic structure incorporated in an aircraft control surface (10) provides a spar (16) extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

An aircraft wingbox assembly is disclosed having a wingbox including an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox, wherein the ribs divide the wingbox into bays; and a fuel tank in the wingbox. All or part of the fuel tank is located in a first one of the bays between a first one of the ribs and a second one of the ribs. The fuel tank includes a tank wall and first and second tank lugs extending from the fuel tank wall. A first fastener attaches the first tank lug to the first one of the ribs; and a second fastener attaches the second tank lug to the second one of the ribs.

A wing leading edge device includes a flow body having a front side, which is delimited by a first spanwise edge and a second spanwise edge, a back side, which is delimited by the first spanwise edge and the second spanwise edge, a front skin arranged on the front side, a back skin arranged on the back side, and at least one stiffening arrangement between the front skin and the back skin in the region of the first spanwise edge, wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement.

An airfoil comprises a wall that defines a leading edge and a trailing edge and one or more cavities located within the wall along with a rib that separates the cavities. The rib or the wall comprises a first split ply that comprises a consolidated section and two or more split sections; wherein the split sections emanate from the consolidated section; and where the split sections define the wall and the cavities of the airfoil.

A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.

A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.