There are provided a metal-resin joint having high bonding strength and a manufacturing method thereof. A metal-resin joint 10 of the present disclosure includes an anchor portion 34 provided on a metal bonding surface 32 of a metal member 30. The anchor portion 34 has a pair of protrusion strips 35 and 35 protruding from the metal bonding surface 32 with a gap, a recessed groove 36 provided between the pair of protrusion strips 35 and 35, and a plurality of partitions 37 protruding from a groove bottom of the recessed groove 36. The plurality of partitions 37 are provided to be inclined toward one side Y1 in a direction in which the pair of protrusion strips 35 and 35 extend as going toward a distal end side, and to be side by side in a direction Y in which the pair of protrusion strips 35 and 35 extend.

An object of the present invention is to obtain a fiber-reinforced composite material achieving both lightweight properties and mechanical properties at a high level. The present invention is a fiber-reinforced composite material including: a resin (A); and a reinforcing fiber (B), and including: a fiber-reinforced structure portion including an in-plane orientation portion having an average fiber orientation angle of the reinforcing fiber (B) of 0° or more and 45° or less and an out-of-plane orientation portion having an average fiber orientation angle of the reinforcing fiber (B) of more than 45° and 90° or less; and a cavity portion defined by the in-plane orientation portion and the out-of-plane orientation portion of the fiber-reinforced structure portion.

A lightning strike protection material for an aircraft includes an electrically-conductive grid with grid-forming members and nodes where grid-forming members overlap or intersect. A plurality of the grid-forming members and/or nodes include an outward-facing surface, and at least a portion of the outward-facing surface is concave.

Problems of high impact resistance and “warpage” of a molded body are solved by a method for producing a molded body, including: using a mold MA and a mold MB, which are a pair of male and female molds, to compression-mold a material A and a material B in contact with the mold MA and the mold MB, respectively, in which the material A contains a carbon fiber and a thermoplastic resin M1, and the material B contains a glass fiber and a thermoplastic resin M2, the molded body includes a pair of side walls and a connecting wall that is connected to the side walls, the molded body has a wave shape in cross section, and a relationship between a flatness Fa of the molded body and a height h of the side wall satisfies 0≤Fa/h<1.3.

A method for bonding thermoplastic fiber-composite parts comprises providing surface texture on one or both parts being bonded, and/or providing both parts with engagement features. Such surface textures and engagement features have a specific geometry and fiber alignment that facilitate fibrous interlock between the two parts at a bonding interface via in-situ consolidation.

A method for bonding thermoplastic fiber-composite parts comprises providing surface texture on one or both parts being bonded, and/or providing both parts with engagement features. Such surface textures and engagement features have a specific geometry and fiber alignment that facilitate fibrous interlock between the two parts at a bonding interface via in-situ consolidation.

A method is disclosed for additively manufacturing a structure. The method may include discharging a composite material, including a reinforcement and a matrix, from a print head, and moving the print head during discharging to form the structure from the composite material. The method may further include exposing the composite material during discharging to a cure energy to trigger the matrix to harden, and selectively adding a filler to the composite material to cause the composite material to increase a temperature achieved when the composite material is exposed to the cure energy.

A forming module for forming a composite laminate part over a tool is provided. The forming module comprises a base, a ply carrier control assembly adapted for controlling the position of a flexible ply carrier on which composite resin plies are mounted, and a head section mounted on the base and adapted for automatically forming the composite resin plies from the ply carrier onto the tool.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

A friction stir spot welding apparatus including a controller that (A) operates a rotary driver and a tool driver such that a pin and a shoulder are brought into contact with a welded workpiece; (B) operates, after the step (A), the rotary driver and the tool driver such that the pin separates from the welded workpiece; and (C) operates, after the step (B), the rotary driver and the tool driver such that the pin advances toward the welded workpiece. The controller controls the tool driver such that pressing force applied to the welded workpiece from the pin and the shoulder in the step (C) is smaller than that in the step (B) and/or controls the rotary driver such that rotational frequencies of the pin and the shoulder in the step (C) are lower than those in the step (B).