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 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.

Provided are a composite structure that is formed by joining a metal member and a molded article of a polyarylene sulfide resin composition and is more excellent in terms of joint strength and heat cycle resistance and a producing method therefor. More specifically, provided are a composite structure formed by joining a surface-roughened metal member and a PPS member, in which a number average value of developed area ratios (Sdr) of an interface measured at five random points on a surface of the surface-roughened metal member using a confocal microscope based on ISO 25178 is 5 [%] or more, and a melt viscosity of a PPS resin is 15 to 500 [Pa.Math.s], and a producing method therefor.

By using a forming die having a fixed die and a movable die moving along a parting surface on the fixed die and by moving the movable die along the parting surface, to press and hold a sintered part between the movable die and the fixed die, to form a cavity around the sintered part except parts which abut on the fixed die and the movable die by the forming die, and to fill the cavity with melted material which becomes an exterior part, so that the sintered part and the exterior part are integrated by insert molding.

A turbomachine blade includes a blading made of composite material with a fibrous reinforcement densified by a matrix and a metal leading edge formed by a metal foil, the foil having an intrados fin and an extrados fin which extend respectively over intrados and extrados faces of the blading by conforming to an airfoil of the blade, wherein the blade also includes at least one unidirectional fabric ply made of composite material on the leading edge between the blading and the metal foil, each unidirectional fabric ply extending at least partially over the intrados and extrados faces of the blading.

By using a forming die having a fixed die and a movable die moving along a parting surface on the fixed die and by moving the movable die along the parting surface, to press and hold a sintered part between the movable die and the fixed die, to form a cavity around the sintered part except parts which abut on the fixed die and the movable die by the forming die, and to fill the cavity with melted material which becomes an exterior part, so that the sintered part and the exterior part are integrated by insert molding.

A method for producing a structural component having a foam structure formed by foaming a foamable material, includes the following steps: additively building a receiving component that reproduces the outer geometry of the structural component to be produced at least in some sections, in particular completely, and having a receiving space for receiving foamable material; introducing at least one foamable material into the receiving space of the receiving component; and carrying out at least one measure for foaming the foamable material introduced into the receiving space of the receiving component so as to form the foam structure.

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 metal resin composite includes a metal substrate, a metal layer formed on a surface of the metal substrate, and a resin layer formed on the metal layer. A plurality of microcracks are formed at a surface of the metal layer.

A vehicle chassis sensor assembly for measuring the ride height of a vehicle which comprises a rotary arm member including an overmolded magnet encapsulated in the rotary arm member. In one embodiment, the overmolded magnet includes a layer of overmold material defining an open overmold window in the side and/or top exterior surfaces of the layer of overmold material. Another embodiment includes a pair of spaced magnets that are completely encapsulated in a two step molding process before being molded into a rotary arm member.