Abstract: A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided.

Abstract: An assembly system for an automated internal assembly on a curved assembly surface of an aircraft fuselage includes two assembly rails shaped in accordance with a curvature of the assembly surface such that they follow a longitudinal direction or a peripheral direction of the aircraft fuselage, so that the assembly rails are fastenable in the aircraft fuselage, along the longitudinal direction or along the peripheral direction of the aircraft fuselage, parallel to one another and parallel to the assembly surface of the aircraft fuselage; an assembly slide configured to slide along the assembly rails; and a tool supported by the assembly slide and configured to perform an assembly step; wherein the assembly slide has an assembly axis, along which the tool is movable relative to the assembly slide; and wherein the assembly axis is configured such that it follows the curvature of the assembly surface of the aircraft fuselage.

Abstract: An aircraft seat with a voltage supply port associated only with the aircraft seat and/or a data port associated only with the aircraft seat, a voltage supply unit, associated with the aircraft seat and including a voltage input and a voltage output, each of which is connected to another of the voltage supply ports, a switching circuit associated only with the aircraft seat and hooked up between the voltage output and the voltage supply port and/or between the data port and a data network, with which each of the voltage supply port or each of the data port can be activated or deactivated.

Abstract: A cabin arrangement for an aircraft, includes a galley monument, which has at least one projection surface, and a projector device by which graphical information can be projected onto the at least one projection surface. Furthermore, an aircraft is described which has at least one such cabin arrangement with the galley monument.

Abstract: A galley monument for an aircraft has a shelf structure, a pull-out member supported on the shelf structure so as to be able to be moved between an insertion position and a deployment position and has a carrier plate, and a display device supported on the pull-out member and having a display. A first surface of the carrier plate in the deployment position of the pull-out member is located in a deployment plane and protrudes with respect to the shelf structure and is located in the insertion position at least partially inside the shelf structure. The display device in the deployment position of the pull-out member can be pivoted about a centre of rotation between a storage position, in which the display device extends parallel with the deployment plane, and a position for use, in which the display device extends transversely relative to the deployment plane.

Abstract: A method of manufacturing a shrouded pipe comprising an inner pipe section for providing a primary fluid path and an outer pipe section for enclosing the inner pipe section to provide a secondary fluid path. The method includes opening the outer pipe section by separating first and second longitudinal edges which split the outer pipe section along a longitudinal line, assembling the outer pipe section with the inner pipe section by passing the inner pipe section between the separated first and second longitudinal edges, and closing the outer pipe section by bringing the first and second longitudinal edges together and joining the first and second longitudinal edges together. An advantage of this method is that close manufacturing tolerances can be achieved without a complex or difficult assembly process.

Abstract: A fastener system for ignition prevention triggered by a lightning strike. The fastener has a fastener body and a fastener head, and a fastening member configured to be mounted on a portion of the fastener body, wherein the fastener and the fastening member are configured to fasten at least a first part and a second part between the fastener head and the fastening member, and the fastener comprises an electrically insulating material. A structure comprises the fastener system, the first part that faces an outside from where the lightning strike may hit the first part and the second part.

Abstract: A communication system for satellite-based communication for an aircraft/spacecraft with data memory, which is configured to store aircraft/spacecraft data during operation of the aircraft/spacecraft, a communication device, which is configured to communicate with at least one satellite-based communication system, and a control device, which is coupled to the data memory and the communication device and is configured to output aircraft/spacecraft data stored in the data memory during operation of the aircraft/spacecraft via the communication device.

Abstract: A press for pressing a component, such as a thermoplastic consolidation and/or forming press, has a first fixed part as a first pressing tool, a movable part as a second pressing tool for pressing a component together with the first pressing tool, and a second fixed part for applying a pressing force to the movable part, wherein the second fixed part and the movable part apply the pressing force generated via interaction between a magnetic field of a pressing magnet and a superconductor cooled below its step temperature.

Abstract: An auxiliary power system for an airplane includes at least one fuel cell unit each with at least one fuel cell, a voltage output, a fuel intake and an outlet for reaction products, a fuel tank that is couplable with the fuel intake of the fuel cell unit, at least one compressor unit with an air intake and air outlet and an electric motor, which is couplable with a voltage output of the at least one fuel cell unit and, by way of a shaft, with the at least one compressor unit. At least the at least one fuel cell unit, the compressor unit and the electric motor are interconnected to yield a coherent unit, which continuously provides electrical power and pressurized air.

Abstract: An aircraft cabin area comprises a door aisle extending between two opposite aircraft doors and an aircraft monument arrangement. The door aisle has a door section adjacent each aircraft door. The monument arrangement comprises a first monument facing the door aisle in a monument section of the door aisle with an access side of the first monument. The monument section extends between the two opposite door sections. The monument arrangement further comprises at least one first trolley parking place for accommodating at least one trolley. The first trolley parking place is provided in the region of the door aisle monument section adjacent the first monument access side to enlarge a base area of the first monument when a trolley is parked therein. Further, at least one second trolley parking place for accommodating at least one trolley is provided in the region of at least one of the door sections.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: Disclosed is a securing device for providing a movable unit of a linear guiding mechanism with additional safety in that the securing device prevents the movable unit from coming off a guiding rail in case of a bearing malfunction. The securing device comprises at least one securing portion and a coupling portion for coupling the at least one securing portion to the movable unit. The securing portion is engageable with the guiding rail in case of a failure of the movable unit.

Abstract: According to an embodiment, a method is provided for preparing a reconditioning of a damaged portion of a component, particularly of an aircraft, by adding an insert, which fills and/or bridges the damaged portion. The method involves: producing a 3D CAD repair model of the damaged portion by scanning; analyzing the repair model and thus evaluating complexity of the damage and/or its reconditioning; as a function of the complexity, deciding between at least two alternative means to perform at least a following step, which is analyzing the repair model and thus dimensioning the reconditioning including the insert. Further, an insert is provided for filling and/or bridging a damaged portion for reconditioning of the damaged portion of a component, particularly of an aircraft, produced according to the method.

Abstract: A conveying device for conveying a fluid stream comprising a mechanical unit, including a movable conveying element, and an electrical unit comprising a housing as well as electronic elements arranged in the housing. The mechanical unit and the electrical unit are detachably connected to one another.

Abstract: A pressure bulkhead for an aircraft fuselage including a sandwich structure defining a central axis and extending between a circumferential border area, the sandwich structure including an inner face sheet and an outer face sheet extending transverse to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet. The pressure bulkhead can receive pressure loads and can be used as a structural bearing element for receiving loads introduced by other structural parts. The inner face sheet and/or the outer face sheet has a corrugated shape. The distance between the outer face sheet and the inner face sheet increases and subsequently decreases from the border area to a central area about the central axis, forming a thickened area where the distance between the outer face sheet and the inner face sheet has a peak.

Abstract: A furnishing item for a vehicle includes a first wall with an access opening situated therein, a door and an oblong flap. The door is arranged on the first wall so that it is swivable relative to the access opening around a first rotational axis. The oblong flap is arranged on the access opening in a vertical direction parallel to the door, and swivelably arranged on a second rotational axis, which is situated on a side of the access opening lying opposite the first rotational axis, and arranged parallel to the first rotational axis. The door and oblong flap extend from the first rotational axis or second rotational axis to the second rotational axis or first rotational axis and together completely close the access opening in a closed state.

Abstract: A method for disinfecting a water system of an aircraft includes the introduction of damp hot air at an inlet of the water system by a ground service unit; flushing of the damp hot air from the inlet through water pipes of the water system to an outlet of the water system; and extraction of the damp hot air at the outlet; wherein the damp hot air is flushed into the inlet and out of the outlet over a predefined disinfection period, and wherein the damp hot air has a temperature between 60° C. and 80° C.

Abstract: A method for disinfecting a water system of an aircraft includes letting-in of hot water at an inlet of the water system by a first ground service unit; flushing the hot water from the inlet, through water pipes of the water system, to an outlet of the water system; and letting-out of the hot water at the outlet, by the first ground service unit or a second ground service unit; the hot water being flushed into the inlet and out of the outlet over a predefined disinfection period; and the hot water being provided at the inlet via a continuous-flow heater of the first ground service unit.

Abstract: An aircraft decompression assembly, comprising a cabin lining element, an element opening and an air channel adjacent to an element rear face and connected to the opening. A channel outlet, during normal assembly operation, discharges air exiting a cabin region delimited by the element through the opening into a secluded area between the element and an aircraft outer skin. A first decompression opening has a first decompression flap, which during normal operation, closes the first decompression opening and, in the event of a rapid decompression, opens the first decompression opening equalizing a pressure between the cabin region and the secluded area. A second decompression opening in the lining element has a second decompression flap which, during normal operation, closes the second decompression opening and which, in the event of a rapid decompression, opens the second decompression opening equalizing a pressure between the cabin region and the secluded area.