Abstract: An autarkic monument in an aircraft pressure cabin supplied with the required operating mediums in a decentralized fashion by carrying along these operating mediums in the monument in operating medium reservoirs is provided. Methods for the efficient energy conversion within this autarkic monument are also provided. The efficiency is achieved such that the energy conversion is, based on the operating mediums, optimized with respect to exergo-economic and/or exergo-ecologic aspects, and such that energy conversion processes are adapted to one another if several energy conversion processes take place.

Abstract: A network access control method involves requesting access to a network via a wireless communication adapter for a personal electronic device. Then, an acoustic audio code output by an audio signaling device connected to the wireless communication adapter by wire is acoustically captured by the personal electronic device. A digital representation of the captured acoustic audio code is submitted from the personal electronic device to the wireless communication adapter via wireless communication. Subsequently, the wireless communication adapter authenticates the personal electronic device on the basis of the submitted digital representation of the captured acoustic audio code.

Abstract: A virtual window assembly for an airborne vehicle includes at least one camera configured to capture a panoramic and time-resolved image data stream from the view to the outside of the airborne vehicle, an image data processor coupled to the camera and configured to receive the captured image data stream and split the image data stream into a plurality of partial image data streams corresponding to different viewing angles of the panoramic image data stream, and a plurality of electronic displays mounted to an inside of a hull of the airborne vehicle, coupled to the image data processor and configured to receive partial image data streams. Each of the electronic displays is configured to display one of the partial image data streams so that the physical mounting location of the electronic displays in the airborne vehicle corresponds to the associated camera viewing angle of the displayed partial image data stream.

Abstract: A new and improved system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes: a first adapter member having a first mating portion that is adhesively bonded with a profile of a first component of the structure in more than one plane, and a first attachment portion connected to the first mating portion; a second adapter member having a second mating portion that is adhesively bonded with a profile of a second component of the structure in more than one plane, and a second attachment portion connected to the second mating portion; and a connector member to securely interconnect the first and second attachment portions of the first and second adapter members.

Abstract: An adhesive retainer for fixing to a structure has at least one adhesive foot which has a supporting base region formed on the adhesive foot and is provided with receiving openings which extend like capillaries through the supporting base region into the interior of the adhesive foot. The receiving openings are configured to form an integral bond with the structure such that when the adhesive foot is placed on the structure covered for this purpose with a liquid, solidifiable bonding substance, the receiving openings receive bonding substance due to capillary ascension.

Abstract: A cable guide arrangement for use in a luggage bin, in particular an aircraft luggage bin, comprises a shaft bearing element and a shaft element rotatably mounted in the shaft bearing element and through which there passes an opening extending along a central axis of the shaft element. The cable guide arrangement further comprises at least one cable guide element connected to the shaft bearing element or to the shaft element and comprising a first and a second guide portion. The first guide portion is configured to deflect a cable, extending in the radial direction with respect to the central axis of the shaft element, with a defined bending radius in the direction of the central axis of the shaft element. The second guide portion is configured to guide the cable parallel to the central axis of the shaft element through the opening extending through the shaft element.

Abstract: A structural component for an aircraft or spacecraft, comprising: a planar member; a reinforcing member which projects from the planar member and is rigidly connected thereto; the reinforcing member comprising at least a foam layer and a cover layer, a plurality of pins extending at least through the foam layer and the cover layer, and at least the pins and the cover layer comprising a curable matrix.

Abstract: A connection box for a system of an aircraft is provided, which includes a plurality of connection boxes, with a holder for holding a line connector for the supply of the system of the aircraft, wherein the system includes, in addition to this connection box, a further connection box with a holder for holding a line connector for the supply of the system of the aircraft. The connection box is configured to receive the further connection box in such a way that both connection boxes can be mounted under an opening in the floor of the aircraft so that both connection boxes are accessible from the opposite side of the floor through the opening in the floor.

Abstract: An arrangement in a cabin of a vehicle includes at least one cabin monument having a first wall and at least one second wall, at least one folding seat with an installation width occupied due to a back side of the folding seat and an installation depth occupied due to a lateral surface of the seat frame of the folding seat, and a delimiting device. At least one of the at least one second walls is arranged at an angle of at least 45° relative to the first wall. At least one of the at least one second walls extends from the first wall at least about the installation depth along der lateral surface of the folding seat. The delimiting device is arranged substantially parallel to the first wall on a side of the second wall farthest from the first wall.

Abstract: A seating arrangement in a cabin of an aircraft includes a floor with a first surface area, a furnishing item with a respective boundary surface, which extends in a vertical direction from the cabin floor, and toward which is directed a first surface area, at least two folding seats, and optionally a partitioning system. The folding seats are arranged on the boundary surface of the furnishing item, and set up to be swiveled into a neutral position and use position, wherein an individual located in the first surface area can sit on the at least two folding seats in the use position. At least one of the at least two folding seats is not designed as a flight attendant seat.

Abstract: Production methods for producing a fiber-reinforced metal component having a metal matrix which is penetrated by a plurality of reinforcing fibers are provided. One method includes depositing in layers reinforcing fibers in fiber layers, depositing in layers and liquefying a metal modelling material in matrix material layers, and consolidating in layers the metal modelling material in adjacently deposited matrix material layers to form the metal matrix of the fiber-reinforced metal component. Here, the metal component is formed integrally from alternately deposited matrix material layers and fiber layers. An alternative method includes introducing an open three-dimensional fiberwoven fabric consisting of reinforcing fibers into a casting mold, pouring a liquid metal modelling material into the casting mold and consolidating the metal modelling material to form the metal matrix of the fiber-reinforced metal component.

Abstract: A system for moving loads comprises a cargo hold floor, at least one row of rollers integrated into the floor, at least one guide rail in the floor and extending parallel to the at least one row of rollers, and a least one transport vehicle. The vehicle is received in the guide rail and movable along the guide rail and comprises at least one connecting element which is movable between first and second operating positions wherein the connecting element, in its first operating position, is arranged such that the vehicle is positionable under a load deposited onto the at least one row of rollers and, in its second operating position, is arranged such that it interacts with the load so as to connect the load to the vehicle such that the load is entrained by the vehicle when the vehicle is moved along the guide rail.

Abstract: Assembling jig for mounting panel structure elements onto a surface of a CFRP-panel, comprising a base frame on which several positioning boards are transversely attached, which are parallel arranged one to another for supporting the CFRP-panel on an upper mounting surface, wherein the base frame comprises at least one metal bar for coupling the positioning boards consisting of a material having a thermal expansion coefficient which corresponds to the thermal expansion coefficient of the CFRP-material of the panel in order to provide a tolerance compensation system in at least longitudinal direction of the base frame.

Abstract: A process for manufacturing a vehicle cabin part (1) to fit in a gap (9) between a first component (5) and a second component (7) including: providing different sealing bodies (3?) each having a first lateral face (11?) conforming to an inner surface (17?) of the first component (5?) and a second lateral face (13?) spaced a certain distance (15?) from the first lateral face (11?); select one of the sealing bodies having a certain distance that fits the gap (9) between the first component (5) and the second component (7); insert the selected sealing body (3) into the gap (9) such that the first lateral face (11) at least partially adjoins the inner surface (17) of the first component (5) and the second lateral face (13) at least partially adjoins the outer surface (21) of the second component (7) facing the first component (5).

Abstract: A residual current protective device for an electric circuit having at least one electrical consumer comprises a residual current determination component, a leakage current determination component and an interruption component. The residual current determination component is configured to determine an amperage difference between the amperage of a current flowing to the at least one electrical consumer and the amperage of a current flowing from the at least one electrical consumer. The leakage current determination component is configured to determine the amperage of a leakage current flowing out of the electric circuit to earth (ground). The interruption component is configured to interrupt the electric circuit if the difference between the determined amperage difference and the determined amperage of the leakage current exceeds a preset limit value.

Abstract: An inerting system for an aircraft includes an inert gas generation apparatus, an air supply line, a compressor and an inert gas line. The compressor supplies the inert gas generation apparatus with air from the air supply line at a pressure necessary for operation of the inert gas generation apparatus. The inert gas line carries the inert gas produced by the inert gas generation apparatus on to an inert gas consumer. The air supply line is connected to an exhaust air system of the aircraft. A method for supplying an inert gas in an aircraft includes tapping of air from an exhaust air system of the aircraft, compression of the tapped air, and production of inert gas in an inert gas generation apparatus from the compressed air. An aircraft is disclosed in which such an inerting system is arranged and/or used.

Abstract: A galley cooling system for an aircraft includes a trolley compartment which includes a cooling unit. A first cooling fluid manifold connects to a cooling fluid outlet or a cooling fluid inlet and has a first cooling fluid manifold wall defining a portion of a lateral boundary of a receiving space of the trolley compartment. A first cooling fluid opening is in the first cooling fluid manifold wall connecting the first cooling fluid manifold to the receiving space of the trolley compartment. A second cooling fluid manifold connected to the cooling fluid inlet or outlet of the cooling unit has a second cooling fluid manifold wall defining a portion of an upper boundary of the receiving space of the trolley compartment, a second cooling fluid opening in the second cooling fluid manifold wall to connect the second cooling fluid manifold to the receiving space of the trolley compartment.

Abstract: A supply system with a plurality of consumers, which can be supplied with a minimum volumetric flow by the supply system to ensure their operational function, wherein the supply system exhibits a network of lines with a plurality of lines, which are each hooked up to the consumers, and a pump connected to the lines for generating a volumetric flow of supply fluid in the lines, wherein the supply system incorporates a network of lines in which consumers are fluidically connected in parallel in relation to the pump arrangement, and wherein each consumer has allocated to it at least one flow control valve functionally placed upstream from the respective consumer in the cooling circulation as viewed from the position of the pump in the direction of flow.

Abstract: A Samer rod has length adjustable along a longitudinal axis. A first element extends along the axis between a first coupling end and an engagement section end, and a second element extends along the axis between a second coupling end and a receiving end. A receiving hole extends along the axis, inside the first element, away from the receiving end to the second coupling end. The engagement section has an outer row of teeth extending parallel to the axis with evenly spaced teeth extending perpendicular to the axis in the circumferential direction of the engagement section. The receiving hole has an inner row of teeth extending parallel to the axis with evenly spaced teeth extending perpendicular to the axis in the circumferential direction of the receiving hole wall. The spacing of the teeth of the two rows in the direction of the axis corresponds to one another.

Abstract: A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.