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.

A cryogenic storage tank including a first metallic end piece having a first structured connection area on its outer surface, a second metallic end piece having a second structured connection area on its outer surface, a hollow body extending between the first structured connection area and the second structured area. The hollow body is formed of a fiber reinforced polymer-based composite, a first metallic clamp having a third structured connection area and a second metallic clamp having a fourth structured connection area. The hollow body is arranged between and in intimate contact with the first structured connection area of the first metallic end piece and with the third structured connection area of the first metallic clamp and is arranged between and in intimate contact with the second structured connection area of the second metallic end piece and with the fourth structured connection area of the second metallic clamp.

A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

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 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.

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 is to provide a metal-resin bonded member that is easy to manufacture and has high bonding strength. The metal-resin bonded member includes a metal body having an iron oxide layer on the surface and a resin body bonded to the metal body via the iron oxide layer. The iron oxide layer has a thickness of 50 nm to 10 μm. The iron oxide layer comprises 60-40 at % Fe and 40-60 at % O at the outermost surface side. The iron oxide layer contains magnetite (Fe.sub.3O.sub.4). The iron oxide layer is formed by heating the surface of an iron-based substrate at 200-850° C. in an oxidation atmosphere. The resin body is composed of polyphenylene sulfide (PPS). The bonding of the metal body and the resin body via the iron oxide layer can be carried out by insert molding, thermal adhesion utilizing friction heating, etc.

A method for manufacturing a composite member, in which a composite member having a high joining strength can be manufactured in an inexpensive and efficient way; and the composite member. A metal member and a resin-containing member are joined together by heating the metal member while pressing the resin-containing member against a metal porous film formed on a surface of the metal member. The porous film is formed by impacting the surface of the metal member with metal powder by the cold spray process.

The disclosure relates to a method of manufacturing a fibre reinforced composite, wherein the surface of the fibre reinforced composite modified by using a laser radiation. In particular, the pre-treatment is performed before a bonding process. Time-consuming and dust generating grinding of the surface can be avoided.

According to an aspect of the present disclosure, A method of manufacturing a composite member including an aluminum member and a resin member that are bonded to each other, the method including: blasting on a surface of the aluminum member to form asperities on the surface of the aluminum member; performing hydrothermal treatment on the surface of the aluminum member having the asperities to modify a surface of the asperities into aluminum hydroxide and form a surface nano structure on the surface of the asperities; applying a binder containing a triazine thiol derivative to the surface of the asperities of the aluminum member modified into aluminum hydroxide and having the surface nano structure to form a coating to be bonded to the aluminum member; and bonding the coating and the resin member.