Abstract: An overhead luggage compartment for a passenger aircraft is provided. The overhead luggage compartment has a receptacle which has a base and two side walls extending from the base. The receptacle can be moved from a closed position into an open position. A device for adjusting a maximum opening width of the receptacle is provided on at least one of the side walls.

Abstract: A coating method wherein in order to simplify the coating method and increase the flexibility thereof with respect to respective desired coatings, provision is made that a powder lacquer layer (3) is applied to a surface (2) of the component (1), and an imprint (4) is applied to the powder lacquer layer (3), preferably by an inkjet method.

Abstract: An overhead luggage compartment for a vehicle cabin is provided. In the compartment, a ledge provided with an electrical component is pivotably held in a housing half-shell about a pivot axis. The pivot axis extends through two axles connecting the ledge to the housing half-shell. For connecting the electrical component to a cable, one of the axles has a through-hole extending in the axial direction, through which the cable is guided for connecting the component.

Abstract: An apparatus for closing a locker, which can be lowered, of a baggage compartment, in particular of an overhead baggage compartment in an aircraft, wherein the locker is connected in an actuating element (5) which is held on a frame (1) such that it can rotate or pivot, and is connected to a gas compression spring (18) in order to assist a closing movement of the locker. In order to allow a completely automatic closing movement, the invention proposes that an electromechanical hybrid drive is provided in order to drive the actuating element (5) and, in addition to the mechanical component of the gas compression spring (18), has an electrical drive apparatus (12) as an electrical component.

Abstract: The invention relates to an actuating device for a luggage locker (1) in an aircraft that has a first operating element (5) that is arranged inside a recess (6) and is capable of transferring the luggage locker (1) from a closed state to an open state for example by way of an electromechanical drive means (7), wherein the electromechanical drive means (7) can transfer the luggage locker (1) from a closed state to an open state via a second operating element (12), wherein the first operating element (5) is coupled to an illuminated display (22) that emits electromagnetic radiation in a wavelength range visible to the human eye in order to display what state the luggage locker (1) is in.

Abstract: The present invention is directed to a luggage storage compartment for an aircraft having high ease of operation. Specifically, the luggage storage compartment comprises a housing and a housing container, with a drive device for moving the housing container between an open position O and a closed position C, with a closure apparatus for locking and unlocking the housing container in the closed position C, and with a control device for controlling the drive device, the control device being designed to actuate the drive device so that said drive device in a relief cycle guides the luggage container first into a relief region R and then into the closed position C, the closure apparatus being lockable or unlockable in a relieved state in the relief cycle.

Abstract: Corresponding to reducing the number of components that need to be separately installed, in addition to a weight reduction and a reduction in the cable loom volume, improved system reliability is obtained if the loads relating to a seating space in a passenger cabin (12), in particular in an aircraft, are combined on an overhead panel (17) which is connected, via line connections which are now only short, to a spatially associated supply module (19), which is operated in cutouts (20) in a stub frame (13), in order to anchor a hat rack (11) in the fuselage structure (16) of the cabin (12).

Abstract: The invention relates to a changing cubicle in an aircraft (14), said changing cubicle comprising outer walls (4) that are opaque, at least in part, and being designed with an access opening (5) that can be closed, at least in part, wherein the changing cubicle (1) can be fastened to an aircraft cabin (9) by a fastening means and can be brought from a first state into a second state, wherein, in the first state, the outer walls (4) of the changing cubicle (1) are collapsed such that passengers can embark or disembark and, in the second state, passengers can change clothes. The invention further relates to a method for retrofitting an aircraft cabin (9) of an aircraft (14) with a changing cubicle (1).

Abstract: A conduit piece for the absorption of foreign bodies in an air distribution conduit of an air-conditioning installation, with a bent portion, the inner wall (I) of which has a large bend radius (Rg) and a small bend radius (Rk). To avoid flow noises according to the invention, an interception device (1, 10, 11, 13, 14) be provided in the region of the large bend radius (Rg) for the purpose of intercepting foreign bodies carried through the conduit piece together with the air.

Abstract: The invention relates to a connection system for elongate hollow bodies (22), in particular pipes or shallow ducts in an aircraft, which includes a first connecting element (2) and a second connecting element (3) which may be mounted on mutually facing ends of elongate hollow bodies (22), wherein the first connecting element (2) includes at least one projecting element (6) which is arranged in a radial direction and, in the event of being pushed together, may be introduced into a corresponding recess (7) in the second connecting element (3), wherein between the first connecting element (2) and the second connecting element (3) there is arranged a locking means (12) which provides a detachable connection between the first connecting element (2) and the second connecting element (3). Furthermore, the invention relates to a method for connecting two elongate hollow bodies, in particular pipes or shallow ducts in an aircraft.

Abstract: The invention relates to an overhead luggage compartment for a passenger aircraft, having a receptacle (2) which comprises a base (B) and two side walls (W) extending therefrom, which receptacle can be moved from a closed position into an open position. A device (3) for adjusting a maximum opening width (O) of the receptacle (2) is provided on at least one of the side walls (W).

Abstract: The invention relates to a window ring for a window of an aircraft, wherein the window ring is substantially formed of a light-guiding substrate, comprises at least one light inlet region to couple light into the substrate, and at least one light exit region which is formed in such a way that light coupled into the substrate exits in it.

Abstract: A fastening device for connecting two overhead storage compartment elements of an aircraft is provided. A passenger service channel (PSC) extends in the overhead storage compartment elements which comprises coupling elements on the sides of the overhead storage compartment elements to be connected, said coupling elements having to be aligned with one another without being subjected to loading. For easy mountability on a first fastening element a connecting plate is arranged in a longitudinally movable manner. In the delivered state of the overhead storage compartment elements, the connecting plate is already connected to the fastening element and pushed beneath the lower face of the overhead storage compartment element, so that it does not protrude thereover and does not interfere when the overhead storage compartment element is handled before attaching to the cabin ceiling.

Abstract: Corresponding to reducing the number of components that need to be separately installed, in addition to a weight reduction and a reduction in the cable loom volume, improved system reliability is obtained if the loads relating to a seating space in a passenger cabin (12), in particular in an aircraft, are combined on an overhead panel (17) which is connected, via line connections which are now only short, to a spatially associated supply module (19), which is operated in cutouts (20) in a stub frame (13), in order to anchor a hat rack (11) in the fuselage structure (16) of the cabin (12).

Abstract: A device for darkening a cabin window, with a drive shaft (11) for moving a first shading member (6), which is guided in two guide rails (3, 4), for to and fro movement, wherein the drive shaft (11) and the guide rails (3, 4) are combined in a common mounting unit.

Abstract: An interior equipment element 2 for vehicle cabins, in particular of aircraft. The interior equipment element 2 consists of at least one first portion 7, on the surface of which there is applied.

Abstract: The present invention is directed to a luminous means comprising at least one light-emitting diode which is at least partly accommodated in a connection block, wherein electrical connections of the at least one light-emitting diode exit from the connection block in an angled fashion relative to the preferred light emission direction (M). The invention is further directed to a cable harness comprising at least one of said luminous means, as well as to an interior trim element comprising said luminous means.

Abstract: The invention relates to an overhead luggage compartment, in particular, for a vehicle cabin, in which a ledge (3) provided with an electrical component is pivotably held in a housing half-shell (1) about a pivot axis, the pivot axis extending through two axles connecting the ledge (3) to the housing half-shell (1). For connecting the electrical component to a cable (9), it is proposed that one of the axles has a through-hole extending in the axial direction, through which the cable (9) is guided for connecting to the component.

Abstract: The invention relates to an overhead luggage compartment, in particular for a vehicle cabin, in which a ledge (2) is held pivotably about a pivot axis in a housing half-shell (1), the ledge (2) being connected to the housing half-shell (1) via at least one damper (3) for damping a pivoting movement, one end (E1) of the damper (3) being attached to a ledge side wall (4) and the other end (E2) of the damper (3) being attached to a damper fastening element (5), which is rotatably attached to the ledge side wall (4) about the pivot axis, and a damper mating fastening element (13) corresponding to the damper fastening element (5) being fixedly attached to a housing half-shell side wall (15) opposing the ledge side wall (4), so that with an engagement of the damper fastening element (5) in the damper mating fastening element (13) a connection which is fixed in terms of rotation is able to be produced between the damper fastening element (5) and the damper mating fastening element (13).

Abstract: The description covers cabin components for aircraft, which can be produced with a sandwich structure and may have the components 1003 for signal and/or power transmission. The cabin components in this case have at least two prepreg layers 1001, 1005 and, for example, a honeycomb layer 1002, which can be connected to one another by pressing and heating. Furthermore, electrical and/or optical signal paths are shown on cabin components, which can be produced by positioning them there or printing. In addition, according to the description, signal and/or power transmission can take place beyond the boundary of cabin components, by means of a transmitter/receiver path.