A composite part is provided and includes a component, a first set of first composite plies with finite lengths and a second set of second composite plies with finite lengths. A respective end of each of the first composite plies is wrapped around the component in a clockwise wrapping direction and includes first fibers. A respective end of each of the second composite plies is wrapped around the component in a counter-clockwise wrapping direction and includes second fibers.

Disclosed is a panel for an aircraft structure, including a laminated skin of layers of metal of which in each case two are joined together by a fibre-reinforced adhesive layer, as well as a laminated doubler of layers of metal and at least one fibre-reinforced adhesive layer in each case between two layers of metal, wherein the doubler has a smaller size of perimeter than the skin and is bonded to an outermost layer of metal of the laminated skin by a fibre-reinforced supplementary adhesive layer, with the feature that at least one part of the perimeter of the fibre-reinforced supplementary adhesive layer is staggered inwards relative to the corresponding perimeter of the doubler and that that part of the inwards-staggered perimeter of the fibre-reinforced supplementary adhesive layer is delimited by a glued edge. Also disclosed is a method for manufacturing such a panel.

A method for manufacturing a sandwich component includes applying at least one matrix material to the upper side and/or the underside of at least one material blank, and arranging the material blanks above one another and/or next to one another. At least two of the material blanks differ in design or matrix material may be applied in different ways along the upper side and/or underside thereof, or matrix material is applied in different ways to at least one of the material blanks along the upper side and/or underside thereof. In that way, at least one horizontal and/or vertical zone of the sandwich component is created having different mechanical properties than other regions of the sandwich component. The material blanks are then pressed to form the sandwich component.

A lightning strike dispersion structure may include a composite component having an outboard surface, wherein the composite component is electrically nonconductive. The lightning strike dispersion structure may include a metal sheet coupled to and extending across a minority portion of the outboard surface of the composite component, wherein the metal sheet is electrically conductive. The lightning strike dispersion structure may also include a metal stud coupled to and in electrical contact with the metal sheet, the metal stud extending completely through the composite component, wherein the metal stud is electrically conductive.

An armor plate is provided having a lamination of an embedded reinforcement basalt fiber mesh within a laminated cast metal alloy; and at least two layers of an aramid fiber. A process to make the armor plate can include suspending a basalt weave within a mold; heating aluminum 6061 or 7075 alloy to a molten state; pouring the molten aluminum into the mold; cooling the resultant matrixed aluminum to ambient temperature; and laminating at least two layers of ballistic fiber to the matrixed aluminum.

An armor plate is provided having a lamination of an embedded reinforcement basalt fiber mesh within a laminated cast metal alloy; and at least two layers of an aramid fiber. A process to make the armor plate can include suspending a basalt weave within a mold; heating aluminum 6061 or 7075 alloy to a molten state; pouring the molten aluminum into the mold; cooling the resultant matrixed aluminum to ambient temperature; and laminating at least two layers of ballistic fiber to the matrixed aluminum.

A composite hybrid gear assembly includes a gear hub formed from a composite material and a gear head assembly. The gear hub includes a shaft region having an axially symmetrical external profile and a hub web region having a flared profile extending from the shaft region. The gear head assembly includes a head web region and a teeth region where the gear head assembly is fixed to the gear hub. Additionally, the composite hybrid gear assembly includes a first sleeve fixed to an external surface of the shaft region. An associated method of making a composite hybrid gear assembly is also provided.

A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

A support structure in a framework construction is provided. The support structure includes a first and a second rod of an axle support of a motor vehicle, a positioning element, and a first and a second fiber winding. The positioning element fixes an alignment of the first rod relative to an alignment of the second rod. A first support section of the positioning element is drawn by the first fiber winding in the direction of a support section of the first rod, and a second support section of the positioning element is drawn by the second fiber winding in the direction of a support section of the second rod in order to hold the first and second rods in the fixed alignment relative to each other by a frictional connection.