First and second composite members each containing first discontinuous fibers of fiber length La, are placed such that end surfaces thereof face each other at an interval of first length L1. Ends of the first and second composite members are melted over a second length L2 from the end surfaces. A connecting member containing second discontinuous fibers of fiber length Lb, is melted and placed to bridge a space between the ends, to form a stack. The stack is pressed, whereby the melted connecting member and the melted end portions flow into the space between the end surfaces to form a mixture portion. The mixture portion is cooled and solidified to produce a fiber-reinforced resin bonded body. The first length L1 is equal to or more than of the fiber length Lb, and the second length L2 is equal to or more than the fiber length La.

A composite reinforcement component for an aircraft or spacecraft, including a first element assembly aligned in a first extension plane, and a second element assembly aligned in a second, perpendicular, extension plane, the second element assembly intersecting the first element assembly at an intersection of the first and second extension planes. The first and second element assembly each have a pair of staggered comb components. Each comb component includes a base and a plurality of rectangular protrusions extending coplanar from the extension planes of the respective element assembly. The rectangular protrusions form comb teeth of one comb component which are overlapping with comb teeth of the other comb component of the pairs of comb components. The comb teeth of the first element assembly are offset along the intersection by a single comb tooth width with respect to the comb teeth of the second element assembly.

The present invention relates to a method for producing thermosetting components from two or more semifinished composite-material products with textile fibre reinforcement and matrix material, wherein the semifinished composite-material products are fully consolidated, with the exception of local regions, and are brought into contact at the partially consolidated (gelled) regions (201, 211, 221, 241) such that the matrix material of the partially consolidated regions (201, 211, 221, 241) bonds and the regions joined together in this way are subsequently fully consolidated. Furthermore, a device which is suitable for producing the semifinished composite-material products is disclosed.

A method of repairing a composite beam having a longitudinal direction including: removing material from a damaged area of the composite beam to form a cut out region; machining a plurality of elongate slots into the composite beam, the elongate slots each having a length in the longitudinal direction of the composite beam and spanning across the damaged area, the elongate slots extending into the composite beam to a depth greater than a depth of the cut out region; introducing a plurality of reinforcing inserts into the respective elongate slots and fixing the reinforcing inserts into the slots with adhesive.

A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aerospace component. An ultrasonic horn is arranged on the thermoplastic patch. The thermoplastic patch is vertically between the thermoplastic aerospace component and the ultrasonic horn. The thermoplastic patch contacts the ultrasonic horn. The thermoplastic patch is continuous ultrasonic welded to the thermoplastic aerospace component using the ultrasonic horn.

A method is provided for joining thermoplastic components. During this method, a skin is provided that is configured from or otherwise includes a skin fiber-reinforced thermoplastic composite. A support member is provided that is configured from or otherwise includes a support member fiber-reinforced thermoplastic composite. A shim is arranged at an interface between the skin and the support member. The shim is configured from or otherwise includes a shim fiber-reinforced thermoplastic composite. The support member is welded to the skin through the shim at the interface.

A wrap film joint structure and a crop wrap film are provided. The wrap film joint structure includes: tear lines provided on a wrap film, and allowing the wrap film to break at the tear lines, where the wrap film breaking at each of the tear lines includes a previous section of the wrap film and a subsequent section of the wrap film; and a connecting layer including a first connecting layer and a second connecting layer; where the first connecting layer is partially connected to the second connecting layer, partially connected to the subsequent section of the wrap film, and partially connected to the previous section of the wrap film; and the second connecting layer is connected to the previous section of the wrap film through a first adhesive layer.

A welded film including, at least a first thermoplastic resin film, a second thermoplastic resin film, and a thermoplastic resin film for connection disposed so as to span between the first thermoplastic resin film and the second thermoplastic resin film, wherein the first thermoplastic resin film and the thermoplastic resin film for connection are welded at a first welded portion, and the second thermoplastic resin film and the thermoplastic resin film for connection are welded at a second welded portion, and the welded portions are separated by 2.0 mm or more, or each of the welded portions is separated from an end portion of the corresponding thermoplastic resin film among the two thermoplastic resin films; and a method of producing the welded film.