There is provided a method for producing a metal-resin composite which includes a resin member and a metal member having a roughened surface in at least a portion of the surface thereof, the resin member being joined so as to be in contact with at least a portion of the roughened surface. The method includes a step of joining the resin member and the metal member by melting the resin member with the frictional heat generated in the surface of the metal member on its side opposite to the resin member in a state where the metal member and the resin member are superposed. The method includes making adjustment so that when the roughened surface is measured at arbitrary five points by using a confocal microscope according to ISO 25178, the developed area ratio (Sdr) is 5 or more in terms of number-average value.

There is provided a method for producing a metal-resin composite which includes a resin member and a metal member having a roughened surface in at least a portion of the surface thereof, the resin member being joined so as to be in contact with at least a portion of the roughened surface. The method includes a step of joining the resin member and the metal member by melting the resin member with the frictional heat generated in the surface of the metal member on its side opposite to the resin member in a state where the metal member and the resin member are superposed. The method includes making adjustment so that when the roughened surface is measured at arbitrary five points by using a confocal microscope according to ISO 25178, the developed area ratio (Sdr) is 5 or more in terms of number-average value.

The present invention discloses a foldable FRP plate, comprising a plurality of first regions and one or a plurality of second regions which are integrated in one piece; the second region is located between two adjacent first regions, so that the adjacent first regions being folded and unfolded relative to each other with the second region as a rotating shaft; the first regions are plate-like products manufactured by impregnating fiber woven fabric with resin for curing, are rigid and cannot be folded; the second region is flexible fiber woven fabric and has a width being two times a design thickness of the FRP plate. The present invention also discloses a manufacturing method, including laying the fiber woven fabric according to a design thickness and a layer layout; dividing the first regions and the second region according to an origami design method.

A system and process for bonding involves a pocket made into one article is used to secure that article to another using a flowable, curable material (e.g., resin) which during saturation enters through a passageway and at least partially fills the void. When the article is cured, the article is bonded to another article to which resin has also been applied since the void (now containing cured material) is larger than the passageway.

A system and process for bonding involves a pocket made into one article is used to secure that article to another using a flowable, curable material (e.g., resin) which during saturation enters through a passageway and at least partially fills the void. When the article is cured, the article is bonded to another article to which resin has also been applied since the void (now containing cured material) is larger than the passageway.

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

Methods and apparatus' for induction welding a first workpiece to a second workpiece at a welding region may include a metallic strip. The metallic strip may be a mesh. The properties of the metallic strip, such as, for example, pore size, thickness, and density, may be configured to conduct heat uniformly across the welding region and prevent eddy current formation across a workpiece. The metallic strip may be embedded in a workpiece or may be fixed to an induction welding tool that acts on the welding region during induction welding. A removable polymer tape may be disposed between a workpiece and a metallic strip fixed to an induction welding tool. The workpieces may be thermoplastic composite structures and thermoplastic composite stiffeners in aircraft structures.

Methods and apparatus' for induction welding a first workpiece to a second workpiece at a welding region may include a metallic strip. The metallic strip may be a mesh. The properties of the metallic strip, such as, for example, pore size, thickness, and density, may be configured to conduct heat uniformly across the welding region and prevent eddy current formation across a workpiece. The metallic strip may be embedded in a workpiece or may be fixed to an induction welding tool that acts on the welding region during induction welding. A removable polymer tape may be disposed between a workpiece and a metallic strip fixed to an induction welding tool. The workpieces may be thermoplastic composite structures and thermoplastic composite stiffeners in aircraft structures.

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.