Abstract: A method for coating a metallic support profile with a layer of a corrosion-resistant material, includes providing the metallic support profile with a surface to be coated, providing a layer element of the corrosion-resistant material adapted to the surface to be coated, applying an adhesive, curable substance to at least one of the surface to be coated and the layer element, applying the layer element to the surface to be coated, covering the arrangement of support profile and layer element by a compacting element, pressing the layer element onto the surface to be coated by the compacting element to achieve a predetermined joint thickness occupied by the adhesive substance, curing the adhesive substance while maintaining the joint thickness to generate a bond, and removing the compacting element.

Abstract: A fuselage component for an aircraft, including a shell part composed of a fiber composite material and a stiffening structure which is connected to an inner surface of the shell part and has shaped parts composed of a fiber composite material, wherein the shaped parts each have a flat base section which extends along the inner surface of the shell part, and a step-shaped profile edge which extends in an encircling manner around the base section. The shaped parts are arranged in the form of parquetry with overlapping profile edges. As a result, the overlapping profile edges form stiffening profiles intersecting at an intersection. Furthermore, an aircraft which has at least one such fuselage component and a method for producing a fuselage component are described.

Abstract: An apparatus for thermally joining thermoplastic fiber composite components includes a pressurization arrangement for jointly covering, at least in a region of a joining zone, thermoplastic fiber composite components to be joined and applying pressure to the thermoplastic fiber composite components to press the thermoplastic fiber composite components against one another, at least in the joining zone, the pressurization arrangement being flexible, at least in some section or sections. A welding device is configured for welding the fiber composite components in the joining zone during pressurization. The pressurization arrangement and welding device are configured to weld the thermoplastic fiber composite components in a pressurized state in the joining zone. The pressurization arrangement is configured to maintain pressurization independently of the welding device until the joining zone solidifies.

Abstract: A method for thermally joining thermoplastic fiber composite components, including jointly covering thermoplastic fiber composite components to be joined, at least in the region of a joining zone, with a pressurization arrangement, which is flexible, at least in some section or sections, and extensive pressurization of thermoplastic fiber composite components to be joined by the pressurization arrangement, with the result that the fiber composite components are pressed against one another, at least in the joining zone. The fiber composite components are welded in the joining zone during pressurization. The pressurization is maintained by the pressurization arrangement until the joining zone solidifies. A cover is also disclosed, in particular a mold or diaphragm, for a pressurization device for thermally joining thermoplastic fiber composite components, and an apparatus for thermally joining thermoplastic fiber composite components.

Abstract: A fuselage component for an aircraft, including a shell part composed of a fiber composite material and a stiffening structure which is connected to an inner surface of the shell part and has shaped parts composed of a fiber composite material, wherein the shaped parts each have a flat base section which extends along the inner surface of the shell part, and a step-shaped profile edge which extends in an encircling manner around the base section. The shaped parts are arranged in the form of parquetry with overlapping profile edges. As a result, the overlapping profile edges form stiffening profiles intersecting at an intersection. Furthermore, an aircraft which has at least one such fuselage component and a method for producing a fuselage component are described.

Abstract: A method for thermally joining thermoplastic fiber composite components, including jointly covering thermoplastic fiber composite components to be joined, at least in the region of a joining zone, with a pressurization arrangement, which is flexible, at least in some section or sections, and extensive pressurization of thermoplastic fiber composite components to be joined by the pressurization arrangement, with the result that the fiber composite components are pressed against one another, at least in the joining zone. The fiber composite components are welded in the joining zone during pressurization. The pressurization is maintained by the pressurization arrangement until the joining zone solidifies. A cover is also disclosed, in particular a mold or diaphragm, for a pressurization device for thermally joining thermoplastic fiber composite components, and an apparatus for thermally joining thermoplastic fiber composite components.