Abstract: A joining method for connecting at least two thermoplastic workpieces is provided to permit the joining even of non-transparent carbon fiber reinforced plastics parts by means of laser welding, in which a splice is produced at the edge regions of the workpieces and the workpieces are subsequently positioned relative to one another in such a manner that the opposite splice regions bound a seam region. Connecting bodies are then inserted into the seam region and heated by means of local heat input by laser beam such that a fixed integrally bonded connection forms between the workpieces and the connecting bodies.

Abstract: A method for connecting components having a fibre-reinforced thermoplastic plastic includes provision of a first component with a first joining surface, provision of a second component with a second joining surface, flush placement of the first joining surface against the second joining surface in order to form a connection joint, placement of a friction stir welding tool against the connection joint, or a surface directly adjacent thereto, of at least one of the components, softening of the first component and the second component, in each case in a region adjacent to the connection joint, by rotation of the tool, such that the thermoplastic plastic of the two components locally fuses, and movement of the tool along the connection joint for the purposes of connecting the two components by formation of a fusion seam, wherein portions of reinforcement fibres are stirred in to increase the strength of the fusion seam.

Abstract: A method for connecting components having a fibre-reinforced thermoplastic plastic includes provision of a first component with a first joining surface, provision of a second component with a second joining surface, flush placement of the first joining surface against the second joining surface in order to form a connection joint, placement of a friction stir welding tool against the connection joint, or a surface directly adjacent thereto, of at least one of the components, softening of the first component and the second component, in each case in a region adjacent to the connection joint, by rotation of the tool, such that the thermoplastic plastic of the two components locally fuses, and movement of the tool along the connection joint for the purposes of connecting the two components by formation of a fusion seam, wherein portions of reinforcement fibres are stirred in to increase the strength of the fusion seam.

Abstract: A joining method for connecting at least two thermoplastic workpieces is provided to permit the joining even of non-transparent carbon fiber reinforced plastics parts by means of laser welding, in which a splice is produced at the edge regions of the workpieces and the workpieces are subsequently positioned relative to one another in such a manner that the opposite splice regions bound a seam region. Connecting bodies are then inserted into the seam region and heated by means of local heat input by laser beam such that a fixed integrally bonded connection forms between the workpieces and the connecting bodies.

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: 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: Lightweight structural component including at least one panel and at least one stiffening element oriented one of lengthwise and crosswise. The at least one stiffening element includes two side pieces. Each of the two side pieces is at least partially connected to the panel in a material-locking manner. The two side pieces are connected to the panel at two separate joint zones. A method of producing the lightweight structural component includes milling the at least one panel to form at least one thickened region and joining the two side pieces to the at least one panel at the two separate joint zones. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

Abstract: The invention relates to a method and a device for laser-beam welding, because the invention is especially suitable for deep welding a wide variety of materials. The object of the invention is to weld a wide variety of materials by means of laser radiation, especially by deep welding, with a reduced amount of work and at the same time good quality of the welded joint produced. The procedure adopted for this according to the invention is that the intensity of the laser radiation is set by beam-shaping in and on the surface of workpieces in such a way that a small area in the workpiece is irradiated with a great intensity, to form a steam capillary there, and a further, larger adjacent area on the workpiece surface is irradiated with a lesser intensity, and as a result a bell-shaped opening of the steam capillary is formed on the workpiece surface and the cooling rate of the melted material is reduced.