A method for forming a composite article includes adding an upper skin at least partially over a failsafe torque tube. The failsafe torque tube includes an inner tube and an outer tube. The method also includes adding a lower skin at least partially under the failsafe torque tube. The upper skin, the lower skin, and the outer tube are made of a composite material. The method also includes co-curing the upper skin, the lower skin, and the outer tube together to produce the composite article.

A flow medium for distributing a resin in vacuum assisted resin transfer molding processes for manufacturing long, thick and more complex composite parts comprises a flow channel encapsulated by a layer of fibrous material, which provides a high volume flow of resin distributed in a timely manner in the mold.

A carbon composite component composed of a plastics-carbon-fiber composite material. The carbon composite component is made up of individual regions, in which at least one ply is composed, in at least a first region, of carbon fibers, and at least one additional region and/or the first region includes a ply which is composed of metal cords which are arranged spaced apart from one another and spatially oriented in at least one direction.

The invention provides a method of manufacturing a metallic-composite joint comprising a metallic component having one hole in a surface thereof, and a metallic fastener having a head portion for attaching to the metallic component and a tail portion for attaching to a composite component, comprising the steps of positioning the metallic fastener such that the head portion of the metallic fastener is retained in the hole, and the tail portion of the metallic fastener extends out of the hole, arranging layered fibers of an uncured composite component on the surface of the metallic component such that the tail portion extends through a gap between adjacent fibers in each fiber layer, and curing the composite component. The invention also provides a metallic-composite joint, a structure, an aircraft structure, an aircraft, a method of manufacturing a fastener assembly, a fastener assembly and a metallic fastener.

A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

The present invention relates to light weight composite materials which comprise a metallic layer and a polymeric layer, the polymeric layer containing a filled thermoplastic polymer which includes a thermoplastic polymer and a metallic fiber. The composite materials of the present invention may be formed using conventional stamping equipment at ambient temperatures. Composite materials of the present invention may also be capable of being welded to other metal materials using a resistance welding process such as resistance spot welding. The invention also relates to methods for producing a sheet of the polymeric layer.

The present invention relates to light weight composite materials which comprise a metallic layer and a polymeric layer, the polymeric layer containing a filled thermoplastic polymer which includes a thermoplastic polymer and a metallic fiber. The composite materials of the present invention may be formed using conventional stamping equipment at ambient temperatures. Composite materials of the present invention may also be capable of being welded to other metal materials using a resistance welding process such as resistance spot welding.

A composite component (130) such as a shear web for a wind turbine blade is described. The component comprises a moulded laminate (44) formed from one or more fibrous layers (40) integrated by resin and defining a laminate edge (48). An edging strip (60) is located adjacent to the laminate edge (48) and is integrated with the laminate. In a particular example, the edging (60) is made from closed-cell foam. Accordingly, resin does not permeate into the bulk of the edging (60) during the moulding process. After the moulding process, a portion (60a) of the edging (60) is removed to reveal an exposed, substantially resin-free surface of the edging which defines a safety edge (64) of the component.

An air vehicle control surface includes an upper skin, a lower skin, a plurality of composite spars extending between the upper skin and the lower skin, and a failsafe torque tube. The failsafe torque tube includes an outer composite tube and an inner tube disposed within the outer composite tube and extending coaxially with the outer composite tube.

A shear web mould system for manufacturing a wind turbine component in form of an I-shaped shear web having a web body and a first web foot flange at a first end of the web body and a second web foot flange at a second end of the web body is described. The system comprises a central moulding portion for forming at least a part of the web body, a first moulding plate for forming at least a part of the first web foot flange, and a second moulding plate for forming at least a part of the second web foot flange. The angles of the first moulding plate and the second moulding plate relative to the central moulding portion are adjustable.