Abstract: A fuselage structure of an aircraft includes a fuselage skin, and a plurality of frame elements spaced apart from one another in a direction parallel to the aircraft longitudinal axis for supporting the fuselage skin. The fuselage skin includes a plurality of interconnected fiber-reinforced composite skin panels that extend between each pair of frame elements and are connected thereto. The composite skin panels further comprise a stiffener integrally formed in each composite skin panel. A method for manufacturing the fuselage skin. The composite skin panels may be interconnected and/or connected to a frame element through an induction welded connection.

Abstract: A device for electromagnetic spot welding of moulded parts includes a pressurizing body, first displacing means configured for moving a pressurizing surface of the pressurizing body against the moulded parts or vice versa to join contact surfaces of the moulded parts to be fused by welding under pressure, an inductor provided in the pressurizing body and configured to generate an electromagnetic field in at least the contact surfaces of the moulded parts, and a mechanical fastener configured to be heated by the electromagnetic field generated by the inductor, or by other means. Second displacing means are configured for moving the mechanical fastener towards the moulded parts and drive the heated mechanical fastener into the joined moulded parts to a position further than the contact surfaces of the moulded parts. A method for electromagnetic welding of moulded parts using the device.

Abstract: A device for electromagnetic spot welding of moulded parts includes a pressurizing body, and first displacing means for moving a pressurizing body against the moulded parts or vice versa to join contact surfaces of the moulded parts to be fused by welding under pressure. The pressurizing body includes an inductor that generates an electromagnetic field in at least the contact surfaces of the moulded parts. A shielding is provided in the pressurizing body around at least a part of the inductor to protect against overheating. A heat sink is provided in the pressurizing body in between the inductor and the pressurizing surface in direct contact with the inductor and the pressurizing surface. The inductor includes cooling means configured for cooling the inductor, the shielding and the heat sink. A method for electromagnetic welding of moulded parts using the device.

Abstract: A fiber-reinforced composite laminate for use in electromagnetic welding of molded parts of said laminates. The laminate has a plurality of structural layers, each formed of electrically conductive fibers embedded in a thermoplastic matrix. Eddy currents may be induced in the electrically conductive fibers by an electrical conductor that generates an electromagnetic field. The structural layers include a first, a second and, optionally, a third pair of two adjacently positioned structural layers. The first pair has an intermediate layer which allows eddy currents to flow between the two structural layers of the first pair. The second pair has an intermediate layer which prevents eddy currents from flowing between the two structural layers of the second pair. The optional third pair does not have an intermediate layer. The laminate shows efficient heating by an electromagnetic field.

Abstract: A tooling for use in a method for electromagnetic welding of two contacted surfaces of molded parts. The tooling includes a rubber body and pressurizing means for pressurizing the rubber body and applying pressure to the contacted surfaces. The rubber body includes an embedded stiff body shaped such as to define different rubber body thicknesses in different directions, which causes a different pressure build-up in the different directions. A method for manufacturing the tooling. The tooling may be used in electromagnetic welding of two contacted surfaces of molded parts by moving a joining inductor along the contacted surfaces, generating an electromagnetic field in an induction-sensitive component of the molded parts to heat a thermally activated coupling means of the molded parts to above a melting temperature of the coupling means.

Abstract: A fuselage structure of an aircraft includes a fuselage skin, and a plurality of frame elements spaced apart from one another in a direction parallel to the aircraft longitudinal axis for supporting the fuselage skin. The fuselage skin includes a plurality of interconnected fiber-reinforced composite skin panels that extend between each pair of frame elements and are connected thereto. The composite skin panels further comprise a stiffener integrally formed in each composite skin panel. A method for manufacturing the fuselage skin. The composite skin panels may be interconnected and/or connected to a frame element through an induction welded connection.

Abstract: A method for joining moulded parts by electromagnetic welding. A joining inductor is moved along contact surfaces of the moulded parts, generating an electromagnetic field in an induction-sensitive component of the moulded part(s) to heat a thermally activated coupling means of the moulded part(s) to above a melting temperature of the coupling means. The strength of the electromagnetic field suitable for joining is determined by previously moving a sensing inductor along the contact plane, generating a relatively weak electromagnetic field to slightly heat the thermally activated coupling means to a sensing temperature, measuring the field strength generated by the sensing inductor in the moulded part(s), determining a discrepancy between the measured field strength of the sensing inductor and the field strength suitable for joining, and adjusting the field strength suitable for joining to close the discrepancy. A device for carrying out the method.

Abstract: A tooling for use in a method for electromagnetic welding of two contacted surfaces of molded parts. The tooling includes a rubber body and pressurizing means for pressurizing the rubber body and applying pressure to the contacted surfaces. The rubber body includes an embedded stiff body shaped such as to define different rubber body thicknesses in different directions, which causes a different pressure build-up in the different directions. A method for manufacturing the tooling. The tooling may be used in electromagnetic welding of two contacted surfaces of molded parts by moving a joining inductor along the contacted surfaces, generating an electromagnetic field in an induction-sensitive component of the molded parts to heat a thermally activated coupling means of the molded parts to above a melting temperature of the coupling means.

Abstract: A method for joining moulded parts by electromagnetic welding. A joining inductor is moved along contact surfaces of the moulded parts, generating an electromagnetic field in an induction-sensitive component of the moulded part(s) to heat a thermally activated coupling means of the moulded part(s) to above a melting temperature of the coupling means. The strength of the electromagnetic field suitable for joining is determined by previously moving a sensing inductor along the contact plane, generating a relatively weak electromagnetic field to slightly heat the thermally activated coupling means to a sensing temperature, measuring the field strength generated by the sensing inductor in the moulded part(s), determining a discrepancy between the measured field strength of the sensing inductor and the field strength suitable for joining, and adjusting the field strength suitable for joining to close the discrepancy. A device for carrying out the method.

Abstract: Method for the production of a laminate and bent product produced from such a laminate. The laminate is made up of at least two outer sheets of metal material with a layer of fibre-reinforced resin between them. During production the fibre layer is applied dry and the layer of resin material is applied around the fibre material only at a later stage. This can take place either by injection or by rendering fluid a layer of resin material that is applied adjoining the layer of fibre material in the laminate. In this way it is ensured that complete filling of the adjacent sheets of metal material with fibre-reinforced resin takes place even in bends.

Abstract: A laminate consisting of at least two metal layers and a fibre-reinforced plastic bonding layer located between the metal layers comprises metal sheets joined to one another. The metal sheets of a metal layer are joined to one another by means of a butt weld. The weld seam determined by the butt weld has a thickness that is at most the same as the thickness of the metal sheets. The metal sheets can consist of Al, Cu, Li, Mg, Si or Ti or an alloy thereof.

Abstract: Method for the production of a laminate and bent product produced from such a laminate. The laminate is made up of at least two outer sheets of metal material with a layer of fibre-reinforced resin between them. During production the fibre layer is applied dry and the layer of resin material is applied around the fibre material only at a later stage. This can take place either by injection or by rendering fluid a layer of resin material that is applied adjoining the layer of fibre material in the laminate. In this way it is ensured that complete filling of the adjacent sheets of metal material with fibre-reinforced resin takes place even in bends.