A vehicle PU composite component having a layered construction having a honeycomb structure, the honeycomb structure being reinforced by PU material, and the layered construction or the component being formed from PU material and having at least one component elevation. The component elevation PU material forming the component elevation differs from the honeycomb structure PU material reinforcing the honeycomb structure, and in that the component elevation PU material has a higher foaming degree having lower material density as compared to the honeycomb structure PU material. A method for producing a vehicle PU composite component having a layered construction having a honeycomb structure.

The present disclosure provides a light-weight flexible high-thermal-conductivity nano-carbon composite film and a method for preparing same. The nano-carbon composite film includes a plurality of composite units laminated sequentially. The, composite unit includes flexible adhesive layers and a graphene film layer, and the flexible adhesive layers are disposed on both sides of the graphene film layer. The preparation method includes sequentially laminating the composite units and hot pressing to obtain the nano-carbon composite film. The nano-carbon composite film has the characteristics of high thermal conductivity, light weight and flexibility, and has an in-plane thermal conductivity of up to 500 W/m.Math.K or higher, a density of 2.0 g/cm.sup.3 or less, and still a thermal conductivity of 500 W/m.Math.K or higher after the nano-carbon composite film is repeatedly bent by 180 for 50 times while there is no peeling of graphene from the surface.

Skin-bonded threaded inserts may be installed within a sandwich panel by curing the insert in place as the sandwich panel is cured. Skin-bonded threaded inserts may include a collar that is transitioned between a raised position and a compressed position during installation of the skin-bonded threaded insert in the sandwich panel, due to compression of the sandwich panel during curing. Skin-bonded threaded inserts may include one or more flanges that engage one or more skins of the sandwich panel. Such flanges may be positioned between two skins, or between the core and a skin of the sandwich panel to secure the sandwich panel in place within the sandwich panel. Skin-bonded threaded inserts may be positioned within a sandwich panel without the use of potting compound and may engage with the skins of the sandwich panel, rather than relying on adherence to the core for sufficient pull-out and shear strength.

A composite member is provided with a bonding member made of a fiber-reinforced resin and a bracket in which the bracket is bonded to the bonding member via a resin. The bracket has a through-hole. The bonding member has a front surface side fiber-reinforced resin sheet and a rear-surface-side fiber-reinforced resin sheet. The front surface side fiber-reinforced resin sheet, the rear surface side fiber-reinforced resin sheet and the bracket are integrally bonded to each other by the resin in a state in which the front surface side fiber-reinforced resin sheet is inserted into the through-hole of the bracket to thereby enhance the bonding strength between the bonding member to the bracket.

The invention relates to a method for fire protection (S) of a part (1) of a gas-turbine engine made of a composite material comprising a main fibrous reinforcement compregnated by a main matrix, the protection method (S) comprising the following steps: preforming (S1) a panel of prepreg (20) such as to grant same a shape corresponding to the shape of a surface (3) of the part (1) to be protected against fire, said panel of prepreg (20) comprising a secondary fibrous reinforcement compregnated by a secondary matrix; applying (S2) the panel of prepreg (20) thus preformed to the part (1); and securing (S3) the panel of prepreg (20) to the surface (3) by thermal treatment of the part (1) provided with said panel of prepreg (20) in order to obtain a fire-protection layer (2).

Provided is an electrical connection system for a wind turbine blade that allows sharing the current between all conductors, in order to avoid voltage differences between them, avoiding internal sparks between pultruded plates, in a spar cap of the wind turbine blade. A second aspect is a wind turbine which in turn includes the wind turbine blade including the electrical bonding system. A third aspect is a method for electrically connecting conductive caps in a wind turbine blade.

An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

A method of forming a cored composite laminate, the method including forming a first recess in a first coupling surface of a first layer of the cored composite laminate, forming a second recess in a second coupling surface of a second layer of the cored composite laminate so that when the first layer of the cored composite laminate and the second layer of the cored composite laminate are coupled, the first recess and the second recess form a cavity through the cored composite laminate, and disposing a shape memory alloy member in the cavity, so that the shape memory alloy member supports the cored composite laminate during curing of the cored composite laminate.

A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

Prepared is a film device (FD) in which a first thermoplastic film (141), a device layer (110) (i.e., a multi-layer product including a polyimide film and a device body), and a second thermoplastic film (142) are arranged. The film device (FD) is pressed against a forming mold (150) and heated at a lower temperature than the temperature limit of the polyimide film, such that the first thermoplastic film is stretched to conform to the shape of the forming mold (150).