A manufacturing method for a joined body, includes: bringing a first member and a second member into contact with each other, at least one of the first member and the second member being made of thermoplastic resin, and the second member having a recessed portion on a joining surface to be joined to the first member; and welding the first member and the second member together, including welding a contact portion of the first member and the second member by melting the thermoplastic resin by frictional heat generated in the contact portion by relative movement of the first member and the second member, in a state in which the first member and the second member are in contact with each other.

A manufacturing method for a joined body, includes: bringing a first member and a second member into contact with each other, at least one of the first member and the second member being made of thermoplastic resin, and the second member having a recessed portion on a joining surface to be joined to the first member; and welding the first member and the second member together, including welding a contact portion of the first member and the second member by melting the thermoplastic resin by frictional heat generated in the contact portion by relative movement of the first member and the second member, in a state in which the first member and the second member are in contact with each other.

A trim part, in particular for covering an airbag in a vehicle, is provided. The trim part comprises at least one outer layer, at least one hinge layer comprising at least one first break line which forms a first part of a perimeter of a flap area and is attached to a first surface of the at least one outer layer, at least one structural layer attached to a first surface of the at least one hinge layer facing away from the at least one outer layer characterized in that at least one of the at least one outer layer comprises a fiber composite material and the at least one structural layer comprises at least one second break line forming a breakthrough area corresponding to the flap area of the at least one hinge layer.

Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.

The present disclosure relates to the technical field of protective case, in particular to a protective case for electronic device and a method for manufacturing the same. The protective case for electronic device includes an inner shell, an outer shell, and a magnetic interlayer that fits and in contact with the inner shell and the outer shell, wherein: the magnetic interlayer includes an interlayer base material and a magnetic part, the magnetic interlayer is provided with a through installation hole, and the magnetic part is fixedly embedded in the installation hole, the thickness of the magnetic part matches with the depth of the installation hole, the interlayer base material includes a hot-melt base material and reinforcing fiber yarn contained in the hot-melt base material, and the hot-melt base material is filled between the magnetic part and the inner side wall of the installation hole.

A pressure tool for applying a pressure force during the welding of plastics components has at least one metallic first component contact section, wherein the pressure tool has at least one elastically deformable second component contact section and is thermally controllable. A Pressure apparatus has at least one such pressure tool for pressing together plastics components during welding. A method for welding plastics components is carried out by such a pressure apparatus and plastics module having at least two welded-together plastics components, wherein the at least two plastics components are welded using such a method.

A pressure tool for applying a pressure force during the welding of plastics components has at least one metallic first component contact section, wherein the pressure tool has at least one elastically deformable second component contact section and is thermally controllable. A Pressure apparatus has at least one such pressure tool for pressing together plastics components during welding. A method for welding plastics components is carried out by such a pressure apparatus and plastics module having at least two welded-together plastics components, wherein the at least two plastics components are welded using such a method.

Systems for defining an internally threaded bore in a composite material component include one or more thread forming tools each defining a thread forming portion and a locating fixture configured to hold the one or more thread forming tools in a predetermined configuration defining a pattern of internally threaded bores to be provided in the composite material component. The thread forming portions include a plurality of thread forming surfaces each defining a pitch, a crest fillet radius, and a root fillet radius, and define internally threaded bores having an interior helical thread defining a plurality of full crest radii and a plurality of full root radii. A component forming fixture is provided for abutting the locating fixture whereby the one or more thread forming tools are held in an interior of the forming fixture. Methods for forming composite material components having internally threaded bores using the described systems are described.

A method for treating a surface of a fibre composite component, wherein an abrasive removal of the surface of the fibre composite component takes place by blasting a removing agent transported by a gaseous transporting fluid onto the surface of the fibre composite component by a feed nozzle and a suction extraction of the removing agent and material removed by the removing agent takes place by an extraction nozzle arranged in the region of the feed nozzle.

A method for treating a surface of a fibre composite component, wherein an abrasive removal of the surface of the fibre composite component takes place by blasting a removing agent transported by a gaseous transporting fluid onto the surface of the fibre composite component by a feed nozzle and a suction extraction of the removing agent and material removed by the removing agent takes place by an extraction nozzle arranged in the region of the feed nozzle.