Abstract: Disclosed is a rotor blade inspection device having a maintenance chamber through which a rotor blade can pass vertically, wherein the floor opening and a roof opening, through which the rotor blade can pass, are arranged in the chamber floor and in the chamber roof of the maintenance chamber, characterized in that the maintenance chamber is arranged on a supporting frame, and in that the bracing frame can be supported on a tower of a wind turbine, and in that the chamber floor and the chamber roof of the maintenance chamber are respectively designed as a diaphragm system in order to minimize a gap between the floor opening or roof opening and the rotor blade.

Abstract: Disclosed is a rotor blade inspection device having a maintenance chamber through which a rotor blade can pass vertically, wherein the floor opening and a roof opening, through which the rotor blade can pass, are arranged in the chamber floor and in the chamber roof of the maintenance chamber, characterized in that the maintenance chamber is arranged on a supporting frame, and in that the bracing frame can be supported on a tower of a wind turbine, and in that the chamber floor and the chamber roof of the maintenance chamber are respectively designed as a diaphragm system in order to minimize a gap between the floor opening or roof opening and the rotor blade.

Abstract: The invention relates to a 1C system and a method for manufacturing semifinished products (prepregs) and components with the 1C system. The problem is solved by a 1C system comprised of an epoxy resin and a secondary amine; the secondary amine is imidazole, an imidazole derivative or a complex of the general formula MeL4X2, wherein Me is a bivalent metal cation selected from copper, cobalt, nickel and zinc, L is a ligand selected from imidazole and an imidazole derivative, and X is an anion selected from fluoride, chloride, bromide, iodide and nitrate. Furthermore, the invention includes a method for manufacturing impregnated semifinished products for the production of duroplastic fiber-reinforced components using a 1C system.

Abstract: The invention relates to a 1C system and a method for manufacturing semifinished products (prepregs) and components with the 1C system. The problem is solved by a 1C system comprised of an epoxy resin and a secondary amine; the secondary amine is imidazole, an imidazole derivative or a complex of the general formula MeL4X2, wherein Me is a bivalent metal cation selected from copper, cobalt, nickel and zinc, L is a ligand selected from imidazole and an imidazole derivative, and X is an anion selected from fluoride, chloride, bromide, iodide and nitrate. Furthermore, the invention includes a method for manufacturing impregnated semifinished products for the production of duroplastic fiber-reinforced components using a 1C system.

Abstract: A radial shaft of a gas-turbine engine which is made up of +/?45° layers, zero layers and +/?30° layers of carbon fiber composite and connected to load-input end pieces via sinusoidal connecting areas.

Abstract: A method for manufacturing a radial shaft of a gas-turbine engine which is made up of +/?45° layers, zero layers and +/?30° layers of carbon fiber composite and connected to load-input end pieces via sinusoidal connecting areas.

Abstract: A radial shaft of a gas-turbine engine which is made up of +/?45° layers, zero layers and +/?30° layers of carbon fiber composite and connected to load-input end pieces via sinusoidal connecting areas.

Abstract: A method for manufacturing a radial shaft of a gas-turbine engine which is made up of +/?45° layers, zero layers and +/?30° layers of carbon fiber composite and connected to load-input end pieces via sinusoidal connecting areas.

Abstract: A stabilizer bar or stabilizer link in fiber composite construction is of a monolithic construction without fiber interruption. The cross section geometry, the wall thickness, and the fiber orientation vary in axial direction and radial direction such that the requirements defined by the available construction space and the expected loads are fulfilled. The fiber orientation is adjusted axially and radially load-appropriately. The middle section of the stabilizer bar that is primarily torsion-loaded is reinforced with fibers oriented between +/?35° and +/?55° relative to the longitudinal axis and the end members that are primarily bending-loaded are reinforced with fibers oriented between +/?20° and +/?40° relative to the longitudinal axis. In the transitional areas between the middle section and the end members there are transitions between these fiber orientations relatively to the longitudinal axis.

Abstract: The invention relates to an aircraft landing gear comprising a landing gear leg, wherein the landing gear leg or one or more parts of the landing gear leg consists partly or completely of a fiber composite material.

Abstract: The invention relates to an aircraft landing gear comprising a landing gear leg, wherein the landing gear leg or one or more parts of the landing gear leg consists partly or completely of a fiber composite material.