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 manufacturing method of a turbomachine airfoil, such as an outlet guide vane airfoil, comprising positioning a first fibrous wall preform on a first mold portion, placing at least one core on the first wall preform, positioning a second fibrous wall preform on the core, assembling a second mold portion to the first mold portion so as to form a mold around the first and second wall preforms, applying a hardening treatment to the first and second wall preforms, removing the core, and positioning a reinforcing structure between the first wall preform and the second wall preform.

A composite of metal and carbon-fiber-reinforced plastic according to the present invention comprising a predetermined metal member, a resin layer positioned at a surface of at least part of the metal member and containing an inorganic filler having a thermal conductivity of 20 W/(m.Math.K) or more, and carbon fiber reinforced plastic positioned on the resin layer and containing a predetermined matrix resin and carbon reinforcing fiber present in the matrix resin, the carbon reinforcing fiber being at least one of pitch-based carbon reinforcing fiber having a thermal conductivity of 180 to 900 W/(m.Math.K) in range or PAN-based carbon reinforcing fiber having a thermal conductivity of 100 to 200 W/(m.Math.K) in range, a content of the inorganic filler in the resin layer being 10 to 45 vol % in range with respect to a total volume of the resin layer, a number density of the inorganic filler present in a region of a width X ?m from an interface of the resin layer and the carbon fiber reinforced plastic in a direction of the resin layer being 300/mm.sup.2 or more, where X ?m is an average particle size of the inorganic filler.

A propeller for a marine propulsion device configured for use on a boat has a hub extending along a longitudinal axis and a plurality of blades, each blade having a blade root attached to the hub and extending radially outwardly from the longitudinal axis toward a respective blade tip, and each blade having a leading edge, a trailing edge, a blade face, and a blade back. Each blade has a polymer-based blade core. A portion of an outer edge of each blade core has a flange that is stepped inwardly from both the blade face and the blade back of the blade core. Each flange is electroless plated with a metal coating that covers the flange and fills in the steps on the blade face and the blade back of the blade core to provide a desired blade section. A method for manufacturing the propeller is also included.

Equipment for forming a tubular rod from a bundle of fibrous material comprising a mandrel constructed to form a space within the bundle of fibres; the mandrel includes a passage for delivering a treatment fluid to facilitate the formation of the fibres into a tubular structure as the fibre bundle as the bundle passes over the mandrel.

A fiber-reinforced resin composite material includes first and second members. The first member includes a first fiber and a first matrix resin. The first fiber includes a reinforcing fiber and is impregnated with the first matrix resin. The reinforcing fiber has a melting point and a tensile strength higher than those of an aliphatic polyamide fiber. The second member includes a stack and a second matrix resin. The stack includes a second fiber and a third fiber filled with the second matrix resin. The second fiber includes the reinforcing fiber. The second matrix resin includes a component common to that of the first matrix resin, and includes a first polyamide resin that includes an aliphatic polyamide resin. The third fiber includes a second polyamide resin that includes an aliphatic polyamide resin and has a melting point higher than that of the first polyamide resin by 7 to 50 degrees centigrade.

An object of the present invention is to provide a prepreg and a laminate for producing a laminate suitable as a structural material, which have excellent joining strength and can be firmly integrated with another structural member by welding. The present invention provides a prepreg including the following structural components: [A] reinforcing fibers, [B] a thermosetting resin, and [C] a thermoplastic resin, wherein [A] has a surface free energy, measured by a Wilhelmy method, of 10 to 50 mJ/m.sup.2, [C] is present on a surface of the prepreg, and the reinforcing fibers [A] are present, which are included in a resin area including [B] and a resin area including [C] across an interface between the two resin areas.

A method of forming a net shape preform for a high performance ballistic helmet includes preparing one or more full prepreg plies, preparing one or more filler prepreg plies, wherein a shape and orientation of one filler prepreg ply of the one or more filler prepreg plies is different from a shape and orientation of another filler prepreg ply of the one or more filler prepreg plies, layering the one or more full prepreg plies with one or more filler prepreg plies to form a ply stack and deforming a portion of the ply stack while constraining the ply stack by applying in-plane tensional force to the ply stack to form the net-shape preform.

A composite yarn fabric which can be suitably used as a material of a fiber-reinforced resin molded article is provided. The composite yarn fabric is obtained by weaving using composite yarns as at least one of the warp or the weft, the composite yarns obtained by doubling and twisting inorganic multifilament yarns and thermoplastic resin yarns. The inorganic multifilament yarns have a mass of 10 to 65 tex, monofilaments constituting the inorganic multifilament yarns have a fiber diameter of 6.6 to 9.5 ?m, a melt flow rate of a thermoplastic resin constituting the thermoplastic resin yarns is 34 to 100 g/10 minutes, and a ratio of a mass of the inorganic multifilament yarns to a total mass of the composite yarns is 40 to 90% by mass.

A system is disclosed for additively manufacturing a composite structure. The system may include a support, and a print head operatively connected to and moveable by the support. The print head may include an outlet configured to discharge a material in a trajectory along a central axis of the outlet; a compactor disposed downstream of the outlet relative to the trajectory and configured to press the material transversely against an adjacent surface, and a cutting module located between the outlet and the compactor. The compactor and the cutting module may be configured to move together relative to the outlet.