Abstract: A power control arrangement for an aircraft galley including a power control unit and an interface unit. A power input of the power control unit includes a main switch and connects to a power feed. Each of a power outlets of the power control unit includes an outlet switch and connects to a galley insert. A main switch interface on the interface unit is provided for switching of the main switch. Each outlet switch interface of the interface unit is associated with one of the outlet switches for switching the outlet switch. The interface unit is arranged remote from the power control unit and the switch interfaces are connected to the corresponding switch via an electrical, radio or optical connection for controlling switching of the switches. Further, an aircraft galley and an aircraft are disclosed.

Abstract: An electrical arrangement on an aircraft fuselage has a fuselage component, an electrical consumer and a conductive electrical connection element. The connection element extends outwardly through an opening in the fuselage component and may have a bearing section on an inside or outside of the fuselage component that is arranged so as to tap or feed a voltage pole. The electrical connection element is electrically insulated from the opening and the fuselage component and is able to be connected to a voltage supply arranged on the inside. The electrical consumer is arranged on the outside of the fuselage component and is electrically connected to that part of the connection element projecting towards the outside of the fuselage.

Abstract: A receiving system for receiving of persons and objects for a cabin of a vehicle is proposed, the system comprising a seat frame having a plurality of receiving sections created on the seat frame for receiving of a seat unit each; a plurality of seat units, which are mountable on a receiving section each; and at least one stowage bin unit, which is mountable on one of the receiving sections. The stowage bin unit is dimensioned such that it is mountable on an outer one of the receiving sections in case on the remaining receiving sections a seat unit each is mounted.

Abstract: A battery has an integrated flame retardant device, wherein the battery has: a cathode layer, a separating layer, and an anode layer, wherein the separating layer is arranged between the cathode layer and the anode layer, wherein the separating layer is impermeable to electrons and permeable to at least one positive type of ion, wherein the separating layer has a flame retardant device having at least one glass fibre, which includes a closed cavity, and wherein a flame retardant is arranged in the cavity. The battery has increased fire resistance.

Abstract: A lavatory for a vehicle includes a housing that is accessible through an access opening, and a washing apparatus for washing feet. The washing apparatus includes a water supply device and a water removal device. The washing apparatus also includes a depression, with which the water removal device is couplable and which is positionable underneath the water supply device. The depression has a use height, which is 700 mm at a maximum.

Abstract: A seat module includes a passenger seat attachable to a cabin floor, and a separate ottoman unit associated with the passenger seat. The ottoman unit has at least one resting surface for a passenger and a base, which base is attachable to the cabin floor by an adjustment unit at a position in a first direction of the passenger seat. The adjustment unit is configured to allow a selective displacement of the ottoman unit relative to the cabin floor along the first direction and at least a second direction perpendicular thereto into a seating position and a resting position of the seat module.

Abstract: Disclosed here is a cargo drive unit for a cargo hold of an aircraft. The cargo drive unit includes at least one driven power transmission element, which is configured to transmit drive forces to a load arranged in the cargo hold, in order to move the load inside the cargo hold. The cargo drive unit also includes a sensor unit configured to acquire at least one movement parameter of the load. The cargo drive unit also includes a control unit configured to control the power transmission element according to the acquired movement parameter. Also disclosed here is a cargo hold that includes such a cargo drive unit, and a related method for operating such a cargo hold.

Abstract: A heated floor panel system for an aircraft, the floor panel system comprising a floor panel element including a panel structure and a panel heater device, a temperature sensor device for detecting the temperature at the floor panel element, and a connector device connected to the floor panel element, wherein the connector device comprises a power link for providing an electric power connection between the panel heater device and an electric power supply, and a data link for providing a data connection between the temperature sensor device and a control unit. An object of the present disclosure, to provide a floor panel system including a floor panel element which has a possibly simple construction and which can be used independently from the connector device, is achieved in that the temperature sensor device is located in the connector device and connected to the floor panel element via a thermal conductor element.

Abstract: An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.

Abstract: A slat track device (7) for an aircraft wing (1) including a beam-shaped main load bearing track structure (9) connected to a slat (5) and movably connected to a main wing (3), a guidance surface (11) at the track structure (9) and guided along a corresponding guidance device (19) at the main wing, a connection device (13) at the track structure (9) connecting the track structure (9) to the slat (5), and an engagement device (15) at the track structure (9) and configured to engage a drive member (33) of a drive unit (37) provided at a main wing (3). The slat track device has redundant main load paths achieved by the track structure (9) having a first track member (41) and a separate second track member (43) both connected to the connection device (13) and the engagement device (15).

Abstract: A vehicle passenger cabin has a holding structure having multiple load introduction points, a multiplicity of support structure parts to be attached to the load introduction points, a lower base for delimiting a lower passenger deck, and a multiplicity of furnishing components to be fastened to the support structure parts. The holding structure has laterally on both sides one floor overhang as a lower delimitation of an upper passenger deck, extending from a laterally outer region of the holding structure radially inwards and at a distance vertically from the lower base. The structure parts are at least regionally curved or bent and are connected at an upper end and at a lower end to an upper and a lower load introduction points, respectively. The structure parts have a first receiving surface for receiving one of the furnishing components, which first receiving surface adjoins the floor overhang radially on the inside.

Abstract: A passenger cabin for a vehicle has an upper passenger deck with an upper arrangement of seats, a lower passenger deck with a lower arrangement of seats, an upper floor for the upper passenger deck arranged between the upper passenger deck and the lower passenger deck, and a lower floor for the lower passenger deck delimiting the lower passenger deck. The upper floor has a central hump region extending along a longitudinal axis of the passenger cabin at least in regions and above which the upper arrangement of seats is arranged, and two side regions adjacent to the hump region. The central hump region is raised relative to the side regions. The lower floor has a lower gangway, wherein the at least one lower arrangement of seats is arranged below the side regions of the upper floor, and the lower gangway is arranged below the central hump region.

Abstract: A system for handling a first component includes: a main-device and a module-device, the module-device having a pressing section arranged to form an outer surface of the module-device, the module-device configured to releasably receive the first component, such that a connection section of the first component is attachable to the pressing section of the module-device. The module-device is releasably connected to a second component, wherein the main-device includes a grabbing unit adapted for releasably connecting the module-device, such that the pressing section is arranged to form a first outer surface section of the main-device, and wherein the main-device includes a connector for connecting to a handling-unit for arranging the main-device at the second component, such that the connection section of the first component, if attached to the pressing section of the module-device, is at least indirectly attachable to a front surface of the second component.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Abstract: A plastics material component for an aircraft includes (i) a substrate, which comprises one or more thermosetting plastics materials, and (ii) one or more layers which are applied to the substrate, at least one layer S1 comprising mica. A method for producing the plastics material component includes providing a substrate including at least one thermosetting plastics material or one polymer which is crosslinked to form a thermosetting plastics material, and applying one or more layers to the substrate, wherein at least one layer includes mica. The mica-containing layer is applied directly to the substrate and the application is carried out before and/or during the curing of the thermosetting plastics material.

Abstract: A method for manufacturing a lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes using an additive manufacturing (AM) or 3D printing technique to form the electric lines on or into a panel body of the lining panel. A lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes a panel body and electric lines being formed on or into the panel body using an AM or 3D printing technique.

Abstract: A system for the additive manufacturing of components includes a powder receptacle, which is designed to receive a powdered material in the form of a starting material for a component to be manufactured, a construction platform that is mounted within the powder receptacle and is mounted so as to rotate relative to the powder receptacle about a rotational shaft, a lowering drive, which is designed to incrementally or continuously lower the construction platform within the powder receptacle, and an energy input apparatus, which is arranged above an opening in the powder receptacle and is designed to carry out locally selective melting or hardening of a powdered material introduced into the powder receptacle on a surface of the material. The construction platform can be tilted by an angle of inclination relative to a rotational shaft of the rotatable mount.

Abstract: An overhead bin for an aircraft comprises a base unit that is designed to fasten the overhead bin to a retaining structure of the aircraft, and a mounting unit that is connected to the base unit. By way of the mounting unit, a stowage space of the overhead bin can be accessed. The base unit provides a first stowage space region, and the mounting unit provides a second stowage space region that together with the first stowage space region forms the stowage space of the overhead bin.

Abstract: A boundary-layer-influencing aerodynamic part comprises a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element, an air guiding layer disposed on the carrier element and a cover layer constituting at least a part of a flow surface and being configured to have air flow there through at least in sections. The air guiding layer is configured to have air flow there through with an air flow supplied to the part, at least in certain operating phases of the part, through the cover layer and flowing in the direction of the carrier element or through the air passage aperture of the carrier element and flowing in the direction of the cover layer. The cover layer is applied directly to the air guiding layer via an additive manufacturing method.

Abstract: A visual output assembly for an aircraft cabin includes at least one electronic display device, a projection screen, an image projector configured to project images onto the projection screen, and at least one illumination device.