The invention is directed to a core material, suitable for use in a closed mold system, based on at least one fibrous web containing a foam-structure within the web, said foam-structure being formed of a plurality of members that are separated from each other by channels, wherein said core material has a compression-resistance of greater than 40% at a pressure of 4 bar and at a temperature that is greater than or equal to 80° C.

A construct for a hockey blade that includes a foam core. The foam core includes a first core face, a second core face, and a bottom core edge and a top core edge. Multiple pins are injected into the foam core, and one or more layers of resin preimpregnated tape are wrapped around the foam before forming a hockey blade structure in a heated mold.

An aircraft wing (6) is provided. The aircraft wing (6) comprises at least one structure (62), (64), 66 comprising: a foam core (626), (666); first and second carbon fibre composite layers (624a), (622a), (662a), (664a) respectively attached to top and bottom sides of the foam core to sandwich the foam core; and third and fourth carbon fibre composite layers (624b), (622b), (662b), (664b) respectively disposed adjacent to the first and second carbon fibre composite layers, wherein the total thickness of the structure is between 1 mm and 11 mm. An aircraft having the aircraft wing and a method of manufacturing a structure are also provided.

A metal-fiber reinforced resin material composite is provided which improves the shear strength between a metallic member and a fiber reinforced material by more strongly bonding the metallic member and the fiber reinforced resin member, and which is very light and has excellent workability while increasing strength.

[Solution]

This metal-fiber reinforced resin material composite is provided with a metallic member and with a fiber reinforced resin material that is stacked on at least one surface of the metallic member and combined with the metallic member, wherein the fiber reinforced resin material comprises a matrix resin containing a thermoplastic resin, a reinforcing fiber material included in the matrix resin, and a resin layer interposed between the reinforcing fiber material and the metallic member and comprising a resin of the same type as the matrix resin. The shear strength of the metallic member and the fiber reinforced resin material is greater than or equal to 0.8 MPa.

A high-pressure tank comprises a liner, a strengthening layer including a first helical layer and a first hoop layer each including a carbon fiber, and a protective layer including a second helical layer and a second hoop layer each including a glass fiber, in this order. The high-pressure tank is provided with a stress-generating portion, a reinforcement layer includes a first area α overlapping the stress-generating portion in a stacking direction and a second area β that is an area except for the first area, and a one-round portion including a final crossing portion at an end of winding of the glass fiber constituting the second hoop layer overlaps the second area in the stacking direction.

A textile fiber-composite material precursor and method for producing a component from fiber-composite material. Aircraft components can be produced from polymer fiber-composite materials, a matrix of which can be a high-performance plastics material such as polyether ketone ketone wherein a reinforcement of a non-crimp fabric of carbon fibers is embedded. Large-area non-crimp fabrics and large-area polymer films can be consolidated while being heated and pressed forming simple components. The flexible textile fiber-composite material precursor includes a stack of woven-fabric tiers from a polymer and of non-crimp fabric tiers from carbon fibers. Since both components are capable of draping, the fiber-composite material precursor can be deposited over a large area on curved shape-imparting surfaces and subsequently be consolidated under pressure and heated to form the fiber-composite material.

Fabrication system and associated methods of fabricating a sandwich panel. In one embodiment, a method includes holding a first skin and a second skin of the sandwich panel with a gap between opposing faces of the first skin and the second skin, and expanding a foamable material between the first skin and the second skin to form a foam core of the sandwich panel.

A method and apparatus for tacking and trimming a thermoplastic tow. A thermoplastic tow is received from a braiding system over a braided structure on a surface. The thermoplastic tow is tack welded to the braided structure. A portion of the thermoplastic tow is trimmed to thereby trim the thermoplastic tow received over the braided structure.

A method of forming a composite product is described. An example of the method comprises providing a layer (34) comprising a sheet-form moulding material and providing a substrate (36). The layer of sheet-form material is applied onto a surface of the substrate (36); and pressed to the substrate in a mould (30). In some examples, the substrate (36) is an open celled foam and gas and/or vapour can be displaced from the pressing region.

A composite structural panel for use in bridge structures, and method of manufacturing same, comprises a top panel and a bottom panel separated by and attached to at least one, but preferably a plurality, of structural composite preforms which may be fabricated by a continuous manufacturing process and may be saturated by resin using a continuous wetting process. The composite preforms may take any cross-sectional shape but are preferably trapezoidal. The top and bottom panels may be fabricated from a plurality of layers of woven fabric layers and non-woven fabric layers which are saturated with a resin that is subsequently cured using cure processes known in the art. The composite structural panel of the invention is usable as a flat structural member for use as bridge decking, ramps, trestles, and any application requiring a structural panel.