The present disclosure relates to a system for manufacturing a hybrid component including a first thermal supplier configured to heat a steel plate, a rolling roll for undercut configured to pressurize the steel plate heated by the first thermal supplier, and to form an undercut on one surface of the steel plate, a first molding roll configured to pressurize the steel plate formed with the undercut to mold the steel plate in a shape of a component to be manufactured, a composite material feeder configured to supply a composite material tape to be seated on one surface of the steel plate formed with the undercut through the first molding roll, and a composite material pressurization roll configured to pressurize the steel plate on which the composite material tape is seated.

A method and apparatus for the additive manufacturing of three-dimensional objects are disclosed. Two or more materials are extruded simultaneously as a composite, with at least one material in liquid form and at least one material in a solid continuous strand completely encased within the liquid material. A means of curing the liquid material after extrusion hardens the composite. A part is constructed using a series of extruded composite paths. The strand material within the composite contains specific chemical, mechanical, or electrical characteristics that instill the object with enhanced capabilities not possible with only one material.

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.

An in-situ fiber-optic temperature field measurement is disclosed that can allow process monitoring and diagnosis for thermoplastic composite welding and other applications. A distributed fiber-optic sensor can be permanently embedded in a thermoplastic welded structure when it is welded and left there to perform lifelong monitoring and inspection. The fiber optic sensor can include a dissolvable coating, or a coating matched to the composite material to be welded. Other applications include in-situ fiber-optic temperature field measurement on thermoset composite curing (autoclave), for thermoplastic and thermoset composites during compression molding, and for fiber-optic field measurements on freeze/thaw of large items of public health interest, such as stored or transported foodstuffs.

A heated composite structure and a method for forming a heated composite structure. The structure includes carbon fibers embedded within a thermoplastic matrix. The carbon fibers are connected with first and second electrodes that are configured to be connected with an electric source such that applying current to the electrodes causes current to flow through the embedded carbon fibers to provide resistive heating sufficient to heat the composite structure to impede formation of ice on the composite structure.

The disclosure discloses a preparation method and product of carbon fiber reinforced polymer composites with a designable characteristic structure. The method includes: (a) choosing carbon fabrics as raw material, where a predetermined number of the fabrics are selected to deposit the reinforcement phase; (b) coating all carbon fabrics with resin matrix, placing the fabrics layer by layer, where the carbon fabrics with the reinforcement phases are placed in a predetermined layer, meanwhile a micro power supply is placed in a setting layer during the stacking process, then a prefabricated product is obtained; (c) placing the prefabricated product in a vacuum bag then evacuating and sealing, hot pressing the sealed prefabricated product, finally the carbon fiber reinforced polymer composite product in the vacuum bag after hot pressing is successfully manufactured.

A molded article of a carbon fiber composite material includes at least carbon fibers and a resin composition. The molded article of a carbon fiber composite material is characterized in that the surface roughness Ra thereof is 0.01-2 ?m and in that the tensile shear adhesive strength (F0) thereof when a metal has been adhered to the surface thereof via an adhesive layer that contains an epoxy compound and is 0.1-3 mm thick is 10-40 MPa.

A method is described for forming a body having at least one through-going passage, said method has the steps of: a) providing a mixture comprising particles and at least one liquid pocket inside a curable matrix, b) subjecting said mixture to a first alternating voltage having a first frequency to form a body in which said at least one liquid pocket extends from a first surface of said body to a second surface of said body thereby forming at least one through-going passage lacking curable matrix, and c) curing said curable matrix into a cured matrix, wherein at least some of said particles are located at an interface between said at least one through-going passage comprising liquid and said cured matrix.

A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

A molding method is provided for manufacturing a composite material having a base layer formed of at least one first prepreg sheet and a second prepreg sheet stacked on at least a portion of the first prepreg sheet. The first prepreg sheet and the second prepreg sheet are stacked, and then heated and cured. The second prepreg sheet constitutes a front surface layer that is integrally formed on the surface of the base layer. Here, the amount of second resin in the second prepreg sheet is larger than the amount of first resin in the first prepreg sheet on a per unit volume basis in an interface between the first prepreg sheet and the second prepreg sheet when the second prepreg sheet is stacked on the first prepreg sheet.