Disclosed are an embedded co-cured composite material with large-damping and electromagnetic wave absorbing properties and a preparation method and an application thereof, belonging to damping composite materials. The embedded co-cured composite material is formed by interlacing a plurality of electromagnetic wave absorbing prepreg layers and a plurality of electromagnetic wave absorbing damping layers. Each of the electromagnetic wave absorbing prepregs layers includes a fiber cloth, a micro-nano electromagnetic wave absorbing material and a resin. Contents of the micro-nano electromagnetic wave absorbing material in the electromagnetic wave absorbing prepreg layers and the electromagnetic wave absorbing damping layers have a gradient increase or decrease according to a sequence of the electromagnetic wave absorbing prepreg layers. Each of the electromagnetic wave absorbing damping layers includes a viscoelastic damping material and the micro-nano electromagnetic wave absorbing material.

An object of the present invention is to provide a fiber-reinforced composite material achieving both lightweight properties and mechanical properties, a laminate thereof, and a prepreg capable of easily molding a sandwich structure thereof. The present invention is a prepreg comprising a reinforced fiber substrate (B) impregnated with a resin (A), wherein the reinforced fiber substrate (B) exists in a folded state having a plurality of folds with a fold angle of 0° or more and less than 90° in the prepreg.

The present disclosure relates to a shaft for athletic activities comprising, along at least a part of the length of the shaft: an internal wall (31) made of a first fiber-reinforced composite; and an external wall (30), fixed to the internal wall, and made of a second fiber-reinforced composite, wherein one or more cavities (32A, 32B, 32C) are present between the internal wall and the external wall.

A composite prepreg and a fiber-reinforced plastic molded body are described that are excellent in secondary weldability with another member and exhibit excellent handleability and reinforcing characteristics, where the composite prepreg in which reinforcing fibers are impregnated with a thermoplastic resin and a thermosetting resin, and a thermoplastic resin layer and a thermosetting resin layer that form an interface and joined to each other are formed, wherein the thermoplastic resin layer is present on at least one surface of the composite prepreg, and the thermoplastic resin layer contains continuous reinforcing fibers.

A method of manufacturing a metal-clad laminate and uses of the same are provided. The method comprises the following steps: (a) impregnating a reinforcement material with a first fluoropolymer solution, and drying the impregnated reinforcement material under a first temperature to obtain a first prepreg; (b) impregnating the first prepreg with a second fluoropolymer solution, and drying the impregnated first prepreg under a second temperature to obtain a second prepreg; and (c) laminating the second prepreg and a metal-clad to obtain a metal-clad laminate, wherein the first fluoropolymer solution has a first fluoropolymer, the second fluoropolymer solution has a second fluoropolymer, and the first fluoropolymer and the second fluoropolymer are different.

The present invention relates to a method for manufacturing a laminate, including: a laminating step of laminating a side of a thermal transfer layer of a thermal transfer sheet having a release sheet and the thermal transfer layer on at least a part of a surface of a resin member by heat bonding, in which the release sheet has no yield points, and has an elongation at break of 100% to 600% in a stress-strain curve measured by a tensile test at a molding temperature Tβ° C. in the laminating step.

A composite laminate structure includes one or more layers of prepreg and a thermoplastic polyurethane film layer on the surface of the one or more prepregs. A method of making a composite laminate structure including a thermoplastic polyurethane film is also provided.

The present invention addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure that is high-quality, low cost, and leaves less voids. The present disclosure addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure with which it is possible to reduce dimples in a composite material skin at low cost. According to a method for molding a composite material structure of the present disclosure, an uncured composite material honeycomb sandwich panel in which prepreg is laminated on upper and lower surfaces of a honeycomb core via an adhesive is covered with a vacuum bag and placed in an autoclave. After that, the vacuum bag is evacuated and, while the evacuation is being continued, is heated and pressurized by the autoclave to cure a matrix resin of the prepreg and achieve adhesion to the honeycomb core.

A method of fabricating a composite material, the method comprises the steps of a) providing a first layer of a fibre reinforced polymer, preferably a thermoset FRP, b) providing an array of thermoplastic islands across at least a proportion of a major surface of the first layer, c) providing a second layer of a fibre reinforced polymer, preferably a thermoset FRP, d) laying the second layer over at least some of the islands, and e) securing the first and second layers together. There is also disclosed a composite which comprises a first layer of a fibre reinforced polymer and a second layer of a fibre reinforced polymer, between which is an intervening layer comprising an array of thermoplastic islands.

A web of impregnated fibrous material(s) including N individual tapes of fibrous material(s) stacked and/or joined in relation to one another, in which said N tapes adhere to each other and can overlap at least partially. The tapes of fibrous material(s) include continuous fibers impregnated with at least one thermoplastic polymer, and optionally a chain extender. The web has a surface, in cross-section perpendicular to the axis of the fibers, S, that is substantially equal to the sum of the surface, in cross-section perpendicular to the axis of the fibers, of each initial individual tape, denoted S.sub.th, S.sub.th being equal to N×l×Ep, wherein l represents the average width of a tape and Ep represents the average thickness of a tape, N being between 2 and 2000, and the average thickness of each individual tape being less than or equal to 150 μm.