In a metal-fiber reinforced plastic (FRP) composite, the FRP and the metal member are bonded together, so internal stress (thermal stress) is generated due to the misfit of coefficients of thermal expansion of the metal member and the FRP. Not only does the binder layer peel off and the mechanical properties of the FRP cannot be obtained, but also defects in appearance (surface strain) occur. Therefore, the technical problem is to secure the mechanical properties as a composite while easing the internal stress and keeping surface strain from being generated.

The metal-fiber reinforced plastic (FRP) composite according to the present invention solves the technical problem by sandwiching an FRP between two metal members and not having at least one of the metal members joined (bonded) with the FRP. Further, it is possible to arrange an intermediate member between the other metal member and the FRP and sandwich the FRP between the two metal members through the intermediate member.

The present invention relates to a method for manufacturing an electronic or electrical system, the method comprising the layer-free production of at least one physical structure (101, 102) which is designed to guide electromagnetic waves, using at least one additively operating apparatus, wherein the layer-free production of the spatial, layer-free structure comprises the simultaneous or sequential application and/or removal of one or more materials in the spatial arrangement, as a result of which the electronic or electrical system is partially or completely formed. The invention further relates to a system which is manufactured in accordance with the method.

The present disclosure relates to an interlayer for being arranged between a first element and a second element of a fibre reinforced composite material, the interlayer comprises an interlayer sheet comprising one or more fibre layers extending in a fibre layer plane, the one or more fibre layers including a first fibre layer comprising a first plurality of fibres and having a first upper fibre surface and a first lower fibre surface, wherein the interlayer sheet has an upper interlayer surface and a lower interlayer surface and wherein the interlayer comprises a plurality of conductive fibres, wherein each of the plurality of conductive fibres forms part of the upper interlayer surface as well as the lower interlayer surface.

The present application relates to a method of forming a structural portion of a fuel tank for an aircraft in which the structural portion is formed from a fibre reinforced polymer and a sensor is integrated in the structural portion. The method includes providing a fibre ply which acts as a structural component, and embroidering an electrically conductive wire in a predetermined pattern on the fibre ply to form the sensor. The fibre ply acts as a sensor substrate. Furthermore, the method includes applying a polymer matrix to the fibre ply so that the fibre ply and electrically conductive wire are covered by the polymer matrix. The present application also relates to a fuel tank for an aircraft, a fuel quantity indicating system, and an aircraft.

Provided are a low dielectric loss non-woven fabric, a preparation method thereof and use thereof. The low dielectric loss non-woven fabric is composed of an inorganic fiber and a binder, and the binder is any one or a combination of at least two of a fluorine-containing resin emulsion, a polyolefin emulsion, a polyphenylene ether resin or a cyanate ester resin. The non-woven fabric of the present application has good dielectric properties and obvious strengthening effect, and can meet various performance requirements for copper clad laminate materials in the field of high-frequency communication.

Provided are a low dielectric loss non-woven fabric, a preparation method thereof and use thereof. The low dielectric loss non-woven fabric is composed of an inorganic fiber and a binder, and the binder is any one or a combination of at least two of a fluorine-containing resin emulsion, a polyolefin emulsion, a polyphenylene ether resin or a cyanate ester resin. The non-woven fabric of the present application has good dielectric properties and obvious strengthening effect, and can meet various performance requirements for copper clad laminate materials in the field of high-frequency communication.

A lightweight radio/CD player for vehicular application is virtually “fastenerless” and includes a case and frontal interface formed of polymer based material that is molded to provide details to accept audio devices such as playback mechanisms (if desired) and radio receivers, as well as the circuit boards required for electrical control and display. The case and frontal interface are of composite structure, including an insert molded electrically conductive wire mesh screen that has been pre-formed to contour with the molding operation. The wire mesh provides EMC, RFI, BCI and ESD shielding and grounding of the circuit boards via exposed wire mesh pads and adjacent ground clips. The major components and subassemblies self-interconnect by integral guide and connection features effecting “slide lock” and “snap lock” self-interconnection. The major components and subassemblies self-ground by establishing an interference fit with exposed, resilient, embossed portions of wire mesh.

A manufacturing method of a reinforced structure includes a step of preparing a stringer that has a fiber exposed surface, a step of disposing an electrically conductive protection member on the fiber exposed surface to cover at least a part of the fiber exposed surface, a step of arranging the stringer on a skin having an uncured resin component, and a step of curing the skin after the arranging. The electrically conductive protection member includes a composite material made of combination of a resin component and an electrically conductive fiber component. The step of curing includes curing the skin and the electrically conductive protection member simultaneously. The manufacturing method can prevent edge glow without increasing the number of production steps.

An aircraft skin panel includes a laminated composite layer and a ground plane coupled to the composite layer, wherein the ground plane is an electrically conductive elastic thermoplastic.

A manufacturing method of a highly flameproof laminated composite material is provided in the present disclosure. The manufacturing method of the highly flameproof laminated composite material includes the steps as follows. A raw material is provided, a shaping step is performed and a combining step is performed. The raw material includes an inorganic powder and a polymer material. In the shaping step, the raw material is made into at least one inorganic layer, an inorganic sheet, a ply of film, or a layer of coating. In the combining step, the inorganic layer is made to be connected to a surface of a substrate, so as to obtain the highly flameproof laminated composite material. A weight ratio of the inorganic powder and the polymer material is 0.01-0.1, and a thickness of the inorganic layer is 0.1 mm-8.0 mm.