Provided is a method for forming a co-cured composite article. The method includes: providing a bag carrier; providing a vacuum bag, wherein the vacuum bag at least partially surrounds the bag carrier; providing an outer skin, wherein the outer skin at least partially surrounds the vacuum bag; forming a space between the bag carrier and the the outer skin; and providing a filler between the outer skin and the bag carrier.

Provided is a method for forming a co-cured composite article. The method includes: providing a bag carrier; providing a vacuum bag, wherein the vacuum bag at least partially surrounds the bag carrier; providing an outer skin, wherein the outer skin at least partially surrounds the vacuum bag; forming a space between the bag carrier and the the outer skin; and providing a filler between the outer skin and the bag carrier.

An open-channel stiffener for stiffening a panel has a bonding flange for bonding the stiffener to the panel through a bondline formed between the bonding flange and the panel to form a stiffened panel. The open-channel stiffener has a cross-sectional shape that aligns, or substantially aligns, a shear center of the stiffener with a centroid of the stiffener and aligns the shear center proximate an edge of the bondline, and removes the need for a radius filler noodle. A plurality of perforations may be formed through the bonding flange to permit an adhesive to wick into the perforations and create a mechanical interlock between the bonding flange and the panel.

A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.

A complex-shaped, three-dimensional fiber reinforced composite trailing edge structure may be formed by using counteracting pressures applied to a structural lay-up of wetted fibers placed onto pressurizable members to form continuous fore and aft loops. In turn, the loops may be structurally functional to transfer loads from the trailing edge structure to a wing center section. The trailing structure may include may include fillers and/or a metallic insert, wherein the metallic insert may provide a lightening strike capability for the trailing edge structure.

A complex-shaped, three-dimensional fiber reinforced composite trailing edge structure may be formed by using counteracting pressures applied to a structural lay-up of wetted fibers placed onto pressurizable members to form continuous fore and aft loops. In turn, the loops may be structurally functional to transfer loads from the trailing edge structure to a wing center section. The trailing structure may include may include fillers and/or a metallic insert, wherein the metallic insert may provide a lightening strike capability for the trailing edge structure.

An aircraft has a wing providing the main lifting surface for the aircraft. The wing has a structure supporting an aero-dynamic surface, and the wing has a weight, the wing structure being unable to support its own weight when the aircraft is stationary and under a load of 1 g so as to cause structural failure of the wing.

A closed-angle composite airfoil spar is provided for an airfoil assembly. The composite airfoil spar comprises a web portion having a thickness. The composite airfoil spar also comprises a flange portion having a thickness. The flange portion extends transverse to the web portion. The composite airfoil spar further comprises a radius portion interconnecting the web and flange portions. The radius portion is an acceptable amount thinner relative to thickness of the web portion and thickness of the flange portion based on design requirements and material properties.

An aerofoil has at least one space frame and at least one pre-stressed cover supported by the space frame. The space frame has one or more structural members, the structural members including a structural foam material; and the pre-stressed cover forms at least a part of an external aerodynamic surface of the aerofoil.

A rib foot cleat for sealing around a stringer passing through a rib mouse hole in an aircraft assembly. The rib foot cleat has a body for attaching to a rib at a rib mouse hole and defines a cleat channel configured to be arranged over the stringer. The rib foot cleat also has an injection hole through the cleat body which is in fluid communication with the cleat channel, to allow sealant material to be injected through the injection hole in to the cleat channel for sealing around the stringer.