Abstract: A sanitary unit for a cabin region on board a vehicle is provided with a first lavatory facility and a second lavatory facility. The first and the second lavatory facilities in each case form a longitudinally-directed interior space comprising two longitudinal sides and two narrow sides. In each case a narrow side comprises an access door. The first and the second lavatory facilities adjoin each other by their longitudinal sides and are separated from each other by a shared middle wall. The shared middle wall extends between lateral connection regions on the narrow sides and comprises at least one offset at least in a middle region between the two lateral connection regions in the horizontal direction.

Abstract: A module for an aircraft has a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane.

Abstract: A device for spatially aligning at least two large-format subassembly components, particularly at least one side shell, at least one upper shell, at least one lower shell and/or at least one floor structure, relative to each other for integrating a component, particularly a fuselage section of an aircraft, is provided which includes: at least two positioning devices for taking up in each case a subassembly component, particularly at least two side shell positioners, at least one upper shell positioner and/or at least one lower shell positioner, at least one measuring device for acquiring a multitude of measured data, particularly of positioning data relating to the subassembly components and/or to the positioning devices, at least one control and/or regulating device, particularly at least one CNC control system, and at least one neuronal network. Moreover, a method for aligning the subassembly components is also provided.

Abstract: The present disclosure relates to a door for a transport means, which structurally provides the largest possible door width. Using a movable carrier arm device, the width of the door aperture can be reduced with little complexity from about 42 inches (Type “A”) as an additional equipment option to about 34 inches (Type “C”). To this end, the movable, for example, foldable, carrier arm device is provided which, when the door opens, automatically moves from a retracted position to an extended position in order to reduce the door aperture width to a value which has been predetermined for evacuation. Afterwards, the extended carrier arm device can be folded in again. In this manner, it may be possible to increase the comfort for the passengers and the crew when the aircraft is in the normal operating state since the carrier arm device provides a greater aperture width in the retracted position.

Abstract: A holder for connecting a module to a component of an aircraft or spacecraft includes a first holder portion having a first adhesive face and a second holder portion having a second adhesive face. The first and second holder portions are movable relative to one another in an initial state of the holder such that a portion of the component can be received between the holder portions so as to glue the holder portions to the component by means of an adhesive layer in each case. The holder has two or more guided parts which are movable relative to one another by means of mutually cooperating guide faces in the initial state of the holder. The guide faces are suitably formed for being glued together using an adhesive. The holder can be used to counter peeling stress of an adhesive connection of the holder in the region of the first and/or second adhesive face.

Abstract: A plug-type mounting is provided for separably connecting an equipment element to a substructure that includes a retainer and a plug element, wherein an interlocking device for engaging the plug element with the retainer is assigned to the retainer and the plug element includes a retaining bolt with a rear bolt ring surface for cooperating with the interlocking device, and wherein the interlocking device includes at least one sliding segment with an arc-shaped interlocking surface.

Abstract: A method for accelerated drying of at least one polymer which is located at least partially on a component, in particular at least a layer of paint and/or a sealing agent which is applied to an aircraft component in particular with a different material composition, involving the following steps of: a) at least partially applying the at least one polymer, in particular an epoxy resin and/or polyurethane-based layer of paint and/or a sealing agent, to an upper side of the component, and b) at least partially drying the polymer by means of electromagnetic radiation with a wavelength range of between 0.28 ?m and 4.0 ?m. Accelerated drying of the polymer, in particular the paint layer thereby becomes possible from an upper side of the component to an upper side of the paint layer.

Abstract: A draining system having an odor seal for a vacuum toilet drain system in which a flexible hose acts as an odor seal. As a result of the flexible hose, propagation of odors can be prevented when the hose collapses flat, for example as a result of its intrinsic weight, and consequently there is no longer a flow-through cross section, wherein, however, drainage of liquids remains possible.

Abstract: A lighting strike protection device for applying automatically to a fiber composite component. The protection device includes a reinforcement structure having a width that is less than a width of the metal strip. The fiber composite component having an integrated lighting strike protection.

Abstract: A beam (20) comprising first and second flanges (23, 24), the beam (20) having a first region (28, 30) extending between the flanges (23, 24) and a second region (26) extending between the flanges. The first region (28, 30) is designed to support an applied concentrated shear load and the second region (26) is designed to support a predominantly bending load. The first region comprises a fan-shaped truss comprising a hub (36) adjacent the first flange and a plurality of struts (37) which extend substantially radially from the hub (36), and the second region (26) comprises either a truss structure which is substantially regular in the longitudinal beam direction or a shear web. The beam may, for example, be used as a floor beam for an aircraft fuselage.

Abstract: A system for the drying of exhaust gases from a fuel cell system includes two heat exchangers alternately exposed to an exhaust gas, which ice and accumulate water vapour from the exhaust gas by cooling through a coolant. A valve arrangement with a number of valves is adapted in such a manner that it operates one of the heat exchangers in an icing phase, in which the icing of water vapour is conducted, and the other heat exchanger in a regeneration phase, in which the accumulated ice melts and is extracted, in an alternating manner. This system is especially suitable in aircraft for drying an oxygen depleted exhaust gas from a fuel cell system for inerting a tank.

Abstract: A habitation and sleeping module, in an aircraft, for accommodating at least one member of a flight crew, with the module having a first sleeping area. Furthermore, an ascent region is provided for ascending from a lower level into the module, wherein the ascent region includes an ascent device that is laterally arranged on the module.

Abstract: A method for the manufacture of a fiber-reinforced thermoplastic composite module from a multiplicity of module components, which are continuously moved in the feed direction and are connected together section-by-section by means of a pressure application head that can be traversed in the feed direction and in the counter-direction. A device for the execution of the method is also disclosed.

Abstract: A regulating system for the regulation of the cabin pressure PC of an aircraft, includes at least one cabin pressure regulator unit, which is so configured that, by controlling at least one air outflow or air inflow device of the aircraft, it can set the cabin pressure Pc within the aircraft fuselage with the latter supplied with fresh air and subjected to pressure at a pressure level or a cabin height defined by the cabin regulator unit. If there are changes to be made to the pressure level or the cabin height, for example while the aircraft is climbing or descending, the cabin regulator unit maintains the quotient of the time-related change of the cabin pressure Pc in the aircraft cabin and the cabin pressure Pc constant. The result is that the gas expansion rate, or the gas compression rate in a passenger's middle ear, remains constant, so that during the entire climbing or descending stage no varying or increasing discomfort is experienced by the passengers.

Abstract: A method and apparatus for producing a hollow component, in particular in the field of aviation or aerospace, including the following steps: provision of an inner contour closed along its circumference; laying of a fiber material over the inner contour; and curing of a matrix of the fiber material to form the component.

Abstract: A sanitary module arrangement configured for installation in an aircraft cabin includes a sanitary module, the interior of which is separated by a partition wall from an area of the aircraft cabin adjacent to the sanitary module. A sanitary appliance and a first trolley parking place to accommodate at least one trolley configured for holding supplies for the passengers in the aircraft cabin are provided in the interior of the sanitary module. A second trolley parking place for accommodating at least one trolley configured for holding supplies for the passengers in the aircraft cabin is provided adjacent to an outer face of the partition wall outside the sanitary module. A trolley fastening device comprises a holder system for detachably fastening a trolley parked at the second trolley parking place, wherein the holder system includes a holder attached to the outer face of the partition wall.

Abstract: A control system for an aircraft high lift device includes a threshold setting unit configured to output one of a plurality of configuration change thresholds as an active output threshold, a threshold deactivation unit coupled to the threshold setting unit and configured to temporarily increase the active output threshold to a deactivation value, a configuration setting unit coupled to the threshold deactivation unit and configured to set the aircraft high lift device from a first configuration to a second configuration, if a measured value of an angle-of-attack of the aircraft exceeds the active output threshold, and a threshold control unit configured to control the threshold deactivation unit to temporarily increase the active output threshold to the deactivation value while the aircraft high lift device is mechanically moving from a first configuration to a second configuration.

Abstract: A priority valve assembly includes a fluid supply line, a first fluid discharge line, and a second fluid discharge line, both of which are to be supplied with fluid via the fluid supply line. A priority valve throttles a fluid flow from the fluid supply line into the second fluid discharge line to prioritize the supply of fluid to the first fluid discharge line over the supply of fluid to the second fluid discharge line if a control parameter which is characteristic for an inlet fluid pressure (pE) in the fluid supply line falls below a first predetermined threshold value (p2). The priority valve reduces the throttling of the fluid flow from the fluid supply line into the second fluid discharge line if the control parameter falls below a second predetermined threshold value (p4) which is smaller than the first predetermined threshold value (p2).

Abstract: A work area is provided for members of a flight crew that includes, but is not limited to a central module, which borders an area adapted for being closed intended for use by crewmembers to change clothes. The central module is arranged in the tail area of the aircraft cabin, and can be used for stowing trolleys. The area is closed by lateral doors, and can be used as a passageway when the doors are open.

Abstract: This relates to an aircraft providing visual signalling of an aircraft. An aircraft for providing visual signalling is provided with at least one multifunctional light unit comprising at least one light source for outboard light emission, which unit is provided on sideway facing areas of the aircraft. The sideway facing areas comprise lateral facing sideway surface areas and/or forward and backwards facing surface areas of the aircraft. The at least one multifunctional light unit is configured to provide i) directional signalling of the aircraft, or ii) status signalling of the aircraft, wherein the status signalling relates to at least one of the group of status of the aircraft, status of the current flight mission, and status of the traffic situation; and/or iii) identification signalling of the aircraft.