Abstract: A device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required is disclosed having an outer structure, a reinforcing plate which is mounted in a predetermined installation region on an inner side of the outer structure and forms a contact surface between the reinforcing plate and the outer structure. The reinforcing plate has a through-opening along the surface normal of the contact surface, and a connecting material which connects the reinforcing plate to the outer structure in an edge region of the contact surface by substance-to-substance bonding and/or by interlocking engagement.

Abstract: An aircraft includes a control computer, load determining unit, first central inertial measurement device and a second inertial measurement device. The load determining unit is coupled to the first inertial measurement device and the second inertial measurement device. The load determining unit can receive instantaneous first accelerations detected by the first inertial measurement device and instantaneous second accelerations detected by the at least one second inertial measurement device and from this to determine instantaneous loads acting on the aircraft and to store them in a memory unit and/or to transmit them to an external unit. The load determining unit can determine expected maneuver accelerations. The load determining unit can subtract the expected maneuver accelerations from detected first accelerations and second accelerations and determine externally induced dynamic accelerations.

Abstract: A composite component system includes a base component with a first component fiber ply and a second component fiber ply and a repair insert with a first repair fiber ply and a second repair fiber ply. The base component is connected to the repair insert by an adhesive joint. The first component fiber ply has an interface surface connected to the interface surface of the first repair fiber ply by the adhesive joint. The second component fiber ply has an interface surface connected to the interface surface of the second repair fiber ply by the adhesive joint. The first component fiber ply has a fiber orientation corresponding substantially to a fiber orientation of the first repair fiber ply. The interface surface of the first repair fiber ply completely overlaps the interface surface of the first component fiber ply.

Abstract: An aircraft includes a control computer, load determining unit, first central inertial measurement device and a second inertial measurement device. The load determining unit is coupled to the first inertial measurement device and the second inertial measurement device. The load determining unit can receive instantaneous first accelerations detected by the first inertial measurement device and instantaneous second accelerations detected by the at least one second inertial measurement device and from this to determine instantaneous loads acting on the aircraft and to store them in a memory unit and/or to transmit them to an external unit. The load determining unit can determine expected maneuver accelerations. The load determining unit can subtract the expected maneuver accelerations from detected first accelerations and second accelerations and determine externally induced dynamic accelerations.

Abstract: A composite component system includes a base component with a first component fiber ply and a second component fiber ply and a repair insert with a first repair fiber ply and a second repair fiber ply. The base component is connected to the repair insert by an adhesive joint. The first component fiber ply has an interface surface connected to the interface surface of the first repair fiber ply by the adhesive joint. The second component fiber ply has an interface surface connected to the interface surface of the second repair fiber ply by the adhesive joint. The first component fiber ply has a fiber orientation corresponding substantially to a fiber orientation of the first repair fiber ply. The interface surface of the first repair fiber ply completely overlaps the interface surface of the first component fiber ply.

Abstract: The invention relates to a plant complex for steel production comprising a blast furnace for producing pig iron, a converter steel mill for producing crude steel and a gas-conducting system for gases that occur when producing the pig iron and/or producing the crude steel. According to the invention, the plant complex additionally has a chemical plant or biotechnological plant, connected to the gas-conducting system, and also energy storage for covering at least part of the electricity demand of the plant complex. Also the subject of the invention is a method for operating the plant complex.

Abstract: The invention relates to a plant complex for steel production comprising a blast furnace for producing pig iron, a converter steel mill for producing crude steel, a gas-conducting system for gases that occur in the production of pig iron and/or in the production of crude steel, and a power-generating plant for electricity generation. The power-generating plant is operated with a gas that comprises at least a partial amount of the blast-furnace top gas that occurs in the production of pig iron and/or a partial amount of the converter gas. According to the invention, a chemical or biotechnological plant is provided and connected to the gas-conducting system and arranged in parallel with the power-generating plant with respect to the gas supply. Externally obtained electricity and power-generating plant electricity are used to cover the electricity demand of the plant complex.

Abstract: The invention relates to a process for preparing ammonia gas and CO2 for urea synthesis. In the process of the invention, a process gas containing nitrogen, hydrogen and carbon dioxide as main components is produced from a metallurgical gas. The metallurgical gas consists of blast furnace gas, or contains blast furnace gas at least as a mixing component. The process gas is fractionated to give a gas stream containing the CO2 component and a gas mixture consisting primarily of N2 and H2. An ammonia gas suitable for the urea synthesis is produced from the gas mixture by means of ammonia synthesis. CO2 is branched off from the CO2-containing gas stream in a purity and amount suitable for the urea synthesis.

Abstract: The invention relates to a process for preparing ammonia gas and CO2 for urea synthesis. In the process of the invention, a process gas containing nitrogen, hydrogen and carbon dioxide as main components is produced from a metallurgical gas. The metallurgical gas consists of blast furnace gas, or contains blast furnace gas at least as a mixing component. The process gas is fractionated to give a gas stream containing the CO2 component and a gas mixture consisting primarily of N2 and H2. An ammonia gas suitable for the urea synthesis is produced from the gas mixture by means of ammonia synthesis. CO2 is branched off from the CO2-containing gas stream in a purity and amount suitable for the urea synthesis.

Abstract: The invention relates to a plant complex for steel production comprising a blast furnace for producing pig iron, a converter steel mill for producing crude steel, a gas-conducting system for gases that occur in the production of pig iron and/or in the production of crude steel, and a power-generating plant for electricity generation. The power-generating plant is operated with a gas that comprises at least a partial amount of the blast-furnace top gas that occurs in the production of pig iron and/or a partial amount of the converter gas. According to the invention, a chemical or biotechnological plant is provided and connected to the gas-conducting system and arranged in parallel with the power-generating plant with respect to the gas supply. Externally obtained electricity and power-generating plant electricity are used to cover the electricity demand of the plant complex.

Abstract: The invention relates to a process for preparing ammonia gas and CO2 for urea synthesis. In the process of the invention, a process gas containing nitrogen, hydrogen and carbon dioxide as main components is produced from a metallurgical gas. The metallurgical gas consists of blast furnace gas, or contains blast furnace gas at least as a mixing component. The process gas is fractionated to give a gas stream containing the CO2 component and a gas mixture consisting primarily of N2 and H2. An ammonia gas suitable for the urea synthesis is produced from the gas mixture by means of ammonia synthesis. CO2 is branched off from the CO2-containing gas stream in a purity and amount suitable for the urea synthesis.

Abstract: The invention relates to a plant complex for steel production comprising a blast furnace for producing pig iron, a converter steel mill for producing crude steel and a gas-conducting system for gases that occur when producing the pig iron and/or producing the crude steel. According to the invention, the plant complex additionally has a chemical plant or biotechnological plant, connected to the gas-conducting system, and also energy storage for covering at least part of the electricity demand of the plant complex. Also the subject of the invention is a method for operating the plant complex.

Abstract: The invention relates to a method for reducing CO2 emissions in the operation of a metallurgical plant which comprises at least one blast furnace for producing crude iron and a converter steel mill for producing crude steel. According to the invention, at least a partial amount of the blast-furnace top gas that occurs in the blast furnace in the production of crude iron and/or a partial amount of the converter gas that occurs in the production of crude steel is taken for producing syngas that is used for producing chemical products. At the same time, the energy demand of the metallurgical plant is at least partly covered by using electricity that is obtained from renewable energy.

Abstract: An aircraft fuselage has an integrated energy-absorbing deformation structure. The fuselage includes annular frames, longitudinal fuselage beams interconnecting the annular frames, and a covering forming a fuselage skin. A lower floor structure is disposed in an interior of the fuselage. The lower floor structure includes a plurality of transverse beams connected to an assigned frame and longitudinal floor beams which interconnect said transverse beams. The deformation structure is formed in a lower fuselage region disposed below the lower floor structure. The deformation structure includes a first inelastically deformable central region and, on a left-hand side and a right-hand side, respective second inelastically deformable regions of greater stiffness in the vertical direction than the central region.

Abstract: An aircraft fuselage has an integrated energy-absorbing deformation structure. The fuselage includes annular frames, longitudinal fuselage beams interconnecting the annular frames, and a covering forming a fuselage skin. A lower floor structure is disposed in an interior of the fuselage. The lower floor structure includes a plurality of transverse beams connected to an assigned frame and longitudinal floor beams which interconnect said transverse beams. The deformation structure is formed in a lower fuselage region disposed below the lower floor structure. The deformation structure includes a first inelastically deformable central region and, on a left-hand side and a right-hand side, respective second inelastically deformable regions of greater stiffness in the vertical direction than the central region.