Abstract: A system and method for manufacturing welded structures comprises components to be welded, a welding additive material which, before the welding, has a shaped profile and the shaped profile is disposed between components to be welded and conforms with at least one of the components to be welded. At least one heat source is used in the method to weld the components, producing a weld seam on at least one side of one of the components.

Abstract: The invention relates to metallic aircraft components which can preferably be used for aircraft structures in the fuselage region. A damage-tolerant design is usual for aircraft components in the fuselage region. It is the object of the invention to provide metallic components in which metal sheets are connected to one another by weld seams which have an improved damage tolerance behavior and fatigue crack propagation behavior. In an aircraft component in accordance with the invention, at least two metal sheets are welded to one another as butt joints. The centerline of the join line of the weld seam is predetermined by the outer edge contour of the metal sheets connected to one another. In this connection, it is formed deviant from a continuously straight line shape such that the total length of the weld seam is increased by changes in direction periodically occurring at the edge contours engaging into one another in a complementary manner.

Abstract: A filler material improves the quality of a joint seam formed during thermal joining of two metallic structural components and includes a core and a coating that surrounds the core at least in sections Because the filler material comprises a coating on the core, the alloying material for the coating may be selected largely independently of any possibly limiting metallurgical requirements in relation to the base material for the core so that with the use of the heterogeneous filler material optimal joint seam characteristics of the joined structural components always result, largely irrespective of the materials composition of the core If an essentially H-shaped cross-sectional geometry of the filler material used, moreover, preliminary fixing or alignment of the structural components that are to be joined in a thermal joining process becomes possible.

Abstract: A system and method for manufacturing welded structures comprises components to be welded, a welding additive material which, before the welding, has a shaped profile and the shaped profile is disposed between components to be welded and conforms with at least one of the components to be welded. At least one heat source is used in the method to weld the components, producing a weld seam on at least one side of one of the components.

Abstract: The invention relates to metallic aircraft components which can preferably be used for aircraft structures in the fuselage region. A damage-tolerant design is usual for aircraft components in the fuselage region. It is the object of the invention to provide metallic components in which metal sheets are connected to one another by weld seams which have an improved damage tolerance behavior and fatigue crack propagation behavior. In an aircraft component in accordance with the invention, at least two metal sheets are welded to one another as butt joints. The centerline of the join line of the weld seam is predetermined by the outer edge contour of the metal sheets connected to one another. In this connection, it is formed deviant from a continuously straight line shape such that the total length of the weld seam is increased by changes in direction periodically occurring at the edge contours engaging into one another in a complementary manner.

Abstract: A system and method for manufacturing welded structures comprises components to be welded, a welding additive material which, before the welding, has a shaped profile and the shaped profile is disposed between components to be welded and conforms with at least one of the components to be welded. At least one heat source is used in the method to weld the components, producing a weld seam on at least one side of one of the components.