A method of producing a composite component (10) having a thermal protection layer (24) including the steps of: providing a composite component (10) with a primary fibre material (12) and with a primer layer (16) of alternative fibre material overlying the primary fibre material (12) at an area of the composite component intended for high thermal exposure, said area defining a thermal exposure area (18); applying a metallic bonding layer (22) to the primer layer (16) of the thermal exposure area (18) to create a bonding surface at the thermal exposure area (18); and applying a ceramic thermal protection layer (24) to the bonding surface for insulating the thermal exposure area (18) and/or for reflecting external thermal energy, the thermal protection layer (24) having a higher melting point than the metallic bonding layer (22).

In manufacturing an electrothermal heater mat, there is provided a preform which comprises a laminated stack of dielectric layers which are made of thermoplastic material and include a central layer or group of layers which include(s) reinforcement and first and second outer groups of layers which do not include reinforcement. The preform includes a heater element and the preform has a first configuration. The preform is then heated to a temperature (e.g. 180 C.) between the glass-transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform is formed into a second configuration which is different to the first configuration so as to produce the heater mat.

This invention relates to a root end structure, a wind turbine blade comprising such a root end structure and a method of manufacturing such a wind turbine blade. The root end structure comprises a plurality of fastening members distributed along a root end of a blade part, wherein a plurality of pultruded elements are arranged in between the fastening members. Each pultruded element has a second side surface facing a first side surface of an adjacent fastening member. Gaps are formed between the first and second side surfaces in at least the thickness direction, wherein the gaps enable an adaptive positioning of the pultruded elements relative to the outer layers during the vacuum assisted resin infusion process.

There is provided a high-pressure tank manufacturing method that ensures a shorten heating period compared with a conventional one and eliminates a need for taking out a material for heating after heating. A high-pressure tank manufacturing method includes: disposing a conductive heating material on an outer periphery of a resin liner; winding a conductive fiber with which thermosetting resin is impregnated around the outer periphery of the resin liner on which the heating material is disposed; and heating the heating material and the fiber on the outer periphery of the resin liner by induction heating to harden the thermosetting resin.

The invention relates to a method for producing a multi-material composite and to a multi-material composite.

Due to the stepwise change of material properties at the interface between different materials, in particular metallic and polymeric materials, cracks often develop in multi-material composites, whereby the service life being shortened.

The method according to the invention is based on a gradual adaptation of the material properties of the materials of a multi-material composite at the interface. A composite is formed from at least one metal layer, at least one fibre-reinforced or unreinforced first polymer layer and at least one fibre-reinforced or unreinforced second polymer layer formed from the polymer of the first polymer layer and nanoparticles, said second polymer layer being at least partially disposed between the metal layer and the first polymer layer, under the influence of elevated temperature or elevated temperature and elevated pressure, wherein nanoparticles of the second polymer layer diffuse into the first polymer layer so that a gradient layer is formed in which the nanoparticle concentration decreases in the direction of the first polymer layer.

The multi-material composite produced by the method according to the invention has a particularly long service life and can be used, for example, in drive shafts for the aviation, automotive, or shipping industry.

Provided is a vacuum assisted resin transfer molding method for producing a component, in particular a spar cap, of a rotor blade including a lightning protection system, wherein the vacuum assisted resin transfer molding method includes the steps of: a) placing) an electrically conductive beam fiber material of an electrically conductive beam, an electrically conductive fiber mat and an electrical conductor of the component in a mold arrangement electrically connecting the electrically conductive beam fiber material to the electrical conductor by means of the electrically conductive fiber mat, wherein an electrical connection between the electrical conductor and the electrically conductive fiber mat is generated, c) subjecting the mold arrangement to underpressure, d) applying an external pressure on the electrical connection from outside the mold arrangement, e) injecting resin into the underpressurized mold arrangement, and f) applying heat to the mold arrangement for curing the resin.

A method for producing a component includes incorporating a molding compound into a tool for producing the component, where the molding compound includes an artificial resin as a matrix and a filler material embedded in the matrix. The method includes compressing the molding compound by the tool and by the compressing forming the molding compound to a green product. The method further includes providing the green product while disposed in the tool with a layer in a sub-region by incorporating a liquid material for producing the layer into the tool and applying the liquid material to the sub-region. The liquid material is a metallic material and the layer is an electromagnetic shielding on the green product.

A form for a vehicle component is provided that includes a commingled fiber bundle composed of a reinforcement fiber. The commingled fiber bundle is laid out in a two-dimensional base layer that defines a shape of the form. A conductive fiber or wire laid in a pattern on the two-dimensional base layer to provide electrical continuity across the form. At least one conductive contact or pad area is built up with overlying layers of the conductive fiber or wire on said two-dimensional base layer. A successive layer is added to embed the conductive fiber or wire and at least one conductive contact or pad area. A conductive fastener is inserted into through hole apertures therein. The conductive fastener is in electrical communication with the corresponding conductive contact or pad area. A method of forming a unitary reinforced composite component is also provided.

A stretchable conductor includes a substrate with a first major surface and an elongate wire, wherein the substrate is an elastomeric material, the elongate wire is on the first major surface of the substrate, the wire includes a first end and a second end, and further includes at least one arcuate region between the first end and the second end. At least one portion of the arcuate region of the wire in the region has a first surface area portion embedded in the surface of the substrate and a second surface area portion unembedded on the substrate and exposed in an amount sufficient to render at least an area of the substrate in the region electrically conductive. The unembedded second surface portion of the arcuate region may lie above or below a plane of the substrate. Additionally, different methods of preparing said stretchable conductor are disclosed. Composite articles including said stretchable conductor in durable electrical contact with a conductive fabric are also disclosed.

A method of forming a hybrid metal composite structure including at least one metal ply. The method includes forming at least one metal ply, forming the at least one metal ply comprising forming at least one perforation in the at least one metal ply, abrasively blasting at least one surface of the at least one metal ply to coarsen the at least one surface of the metal ply, and exposing the at least one metal ply to at least one of an acid or a base. The method further includes disposing at least one fiber composite material structure adjacent the at least one metal ply. Related methods of forming a portion of a rocket case and related hybrid metal composite structures are also disclosed.