Abstract: A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes inducing compressive residual stresses in a first area of the first joint region for preventing cracks by applying parallel crack retarding regions formed as stripes in the first area, drilling fastener holes in the first and second areas of the first. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint.

Abstract: A vehicle structure component reinforced by means of an area, a vehicle including such a vehicle structure component, and a corresponding method to reinforce a vehicle structure component are proposed. The area includes a compressive residual stress in a first direction and a compressive or tensile residual stress in a second direction being vertically aligned to the first direction, wherein the ratio of the compressive stress in the first direction and the compressive or tensile residual stress lies between ?0.2 and +1.0. Hence, the propagation direction of cracks in such areas is diverted, faster pressure equalization takes place, and further crack propagation is inhibited.

Abstract: A solid overlay for laser shock peening is described herein. The solid overlay includes a transparent or translucent material, wherein the solid overlay is structured and adapted to a shape of a surface of a component to be treated by the laser shock peening. The solid overlay is configured to confine a plasma plume generated by laser light.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes a step of providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes a step of inducing compressive residual stresses in a first area of the first joint region for preventing cracks. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint. An aircraft including first and second aircraft structural parts is also described.

Abstract: A fastener comprising a shaft having a first end and a second end, the fastener comprising a head at a first end of the shaft, the shaft defining either a radially extending recess between the first and second ends and/or a head with regions having different radii of curvature.

Abstract: The present invention provides a method for preventing the forming of cracks and slowing the crack propagation in metallic airplane structural parts by laser shock peening with the following steps: Providing an airplane structural part having a crack; irradiating a first surface area of the airplane structural part close to the crack with a first pulsed laser beam having a first wavelength and a first pulsation frequency, wherein energy of the first laser beam is absorbed by the airplane structural part and a shock wave runs through the airplane structural part, which creates compressive prestressings in the airplane structural part.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A method of fabricating a module for an airframe or fuselage structure of an aircraft or spacecraft includes positioning a first member adjacent to a second member at an assembly station; welding the first member to the second member at the assembly station to produce a module having a welded joint between the first and second members; and peening at least one of the first member, the second member, and the welded joint at the assembly station to compensate for or to correct distortion caused by the welding.

Abstract: A vehicle structure component reinforced by means of an area, a vehicle including such a vehicle structure component, and a corresponding method to reinforce a vehicle structure component are proposed. The area includes a compressive residual stress in a first direction and a compressive or tensile residual stress in a second direction being vertically aligned to the first direction, wherein the ratio of the compressive stress in the first direction and the compressive or tensile residual stress lies between ?0.2 and +1.0. Hence, the propagation direction of cracks in such areas is diverted, faster pressure equalization takes place, and further crack propagation is inhibited.

Abstract: In the case of a method for connecting a fibre composite component to a structural component of an aircraft and spacecraft, a metal foil is provided as a transverse reinforcement element between the fibre composite component and the structural component. It is formed with at least one anchoring portion which protrudes from the surface facing the fibre composite component and is inserted between the fibre composite component and the structural component. A corresponding arrangement is produced in accordance with this method.

Abstract: The present invention provides a method for preventing the forming of cracks and slowing the crack propagation in metallic airplane structural parts by laser shock peening with the following steps: Providing an airplane structural part having a crack; irradiating a first surface area of the airplane structural part close to the crack with a first pulsed laser beam having a first wavelength and a first pulsation frequency, wherein energy of the first laser beam is absorbed by the airplane structural part and a shock wave runs through the airplane structural part, which creates compressive prestressings in the airplane structural part.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.