Abstract: The invention provides a method and apparatus for forming a freeform metal structure by wire feed additive manufacturing. In accordance with the method, a holding structure is moved in at least one moving direction, the holding structure holding the metal structure. A metal wire end is fed along an area of deposition on the metal structure in the at least one moving direction. The metal wire end is heated to a melting temperature using a heat source, with the metal wire end as melted being deposited on the metal structure as a metallic build-up material. The metallic build-up material after heating and during the cooling is subjected in the at least one moving direction behind the area of deposition to at least one pulsed magnetic field using a magnetic coil arranged after the heat source, the at least one pulsed magnetic field effecting plastic deformation of the build-up material.

Abstract: The invention provides a method and apparatus for forming a freeform metal structure by wire feed additive manufacturing, wherein a metal wire end is moved along an area of deposition and is melted by a heat source, the melting being deposited on the metal structure as a metallic build-up material, wherein during the cooling process build-up material is subjected to at least one pulsed magnetic field effecting plastic deformation of the build-up material.

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: 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: The extensometer comprises a basic body (18) which carries two tap legs (12) which abut a specimen (16) to be measured so as to be frictionally locked thereto. Due to the frictional contact, the tap legs (12) move relative to each other when the specimen is subjected to external stresses. Via a signal transmitter (24), this movement of the tap legs (12) is detected. The extensometer (10) is floatingly supported by introducing gas in the clearance between a baffle body (36) connected to the extensometer (10) and a stationary support member (28) toward the baffle body (36). On the one hand, the upbuilding gas cushion presses the extensometer (10) with its tap legs (12) against the specimen (16) so as to be frictionally locked thereto and, on the other hand, permits pivoting of the extensometer (10) corresponding to the movement of the measuring points.