Abstract: A device for attaching an object to an attachment rail, particularly a seat rail, in an aircraft or spacecraft. A base part has a support surface to be placed onto an outer surface of the rail, and a locking element to partially protrude from the support surface along a line of protrusion. The base part and locking element are coupled or configured to be coupled wherein the locking element can be moved relative to the base part along the line of protrusion and rotated with respect to the base part. An end section of the locking element has a tip portion shaped in a dovetail-type manner. The device includes a tensioning arrangement for tensioning the locking element with respect to the rail. An arrangement includes such a device as well as an attachment rail with a rail main body and a plurality of bushes. A method for attaching an object, and a seat rail are disclosed.

Abstract: A multimedia distribution network, useful on board a passenger aircraft, includes a first network node configured as a head controller, a plurality of second network nodes configured as intermediate controllers connected to the first network node, and a plurality of third network nodes configured as end device controllers, each connected to one of the second network nodes. The head controller is configured to transmit a multicast stream of multimedia control signal packets to control the end device controllers to the intermediate controllers. The intermediate controllers are configured to periodically transmit unicast delay queries to the head controller, to process the received multimedia control signal packets to the end device controllers and to distribute processed multimedia control signal packets with a controllable delay based on the content of unicast delay indicator signals sent by the head controller to the intermediate controllers in response to the unicast delay queries.

Abstract: A filling level monitoring device for monitoring a filling level of a fluid in a container includes exciter(s), sensor(s), a signal source connected to the exciter(s), a processor, at least one spatial orientation and acceleration sensor, and a filling level indicator. The device uses the signal source and the exciter(s) to couple vibrational loads having multiple frequency components into the container. Sensors measure vibrations in the container after the exciters transmit the vibrational loads into the container. The processor performs spectral analysis of the input signal and of vibration signals from the sensors, comparing these respective spectral functions to extract resonance frequencies of the container, which are based on the spatial orientation of the container.

Abstract: A seat rail assembly for fastening a seat assembly in a vehicle and a method for making such a seat rail assembly are described. The seat rail assembly includes a seat rail configured to fasten the seat assembly, the seat rail including a metal material. A fastening profile element of the seat rail assembly is configured to receive the seat rail, the fastening profile element being formed of a plastic material. The fastening profile element forms a receiving region, which is configured to receive the seat rail, and the seat rail includes a seat rail crown which is arranged in the receiving region of the fastening profile element such that a wall portion of the fastening profile element at least partly extends around the seat rail crown. The seat rail assembly may be used in an aircraft.

Abstract: A wing (5) for an aircraft (1) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement (27) between two supports (23, 25) and having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position to prevent a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7). One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which is destroyed when loads transmitted through the hold down elements (29, 31) exceed a threshold. Once destroyed, the trailing edge (22) of the high-lift device (15) is not prevented from detaching from the upper surface (19).

Abstract: A solid oxide fuel cell stack for an aircraft engine includes ring-shaped fuel cell assemblies of parallel tubular oxide fuel cells circumferentially around a central axis. A first stacking manifold for each fuel cell assembly is in contact with a first side of the individual fuel cell assembly, a second stacking manifold is in contact with a second side of the individual fuel cell assembly, and a central recess for leading an engine shaft through. Each fuel cell includes a tubular anode and tubular cathode, the fuel cell assemblies stacked in an axial direction through pairs of first and second stacking manifolds contacting each other. Each first stacking manifold includes a hydrogen inlet and is connected to first ends of the anodes of the fuel cells. Each second stacking manifold includes a hydrogen and steam outlet and is connected to second ends of the anodes of the fuel cells.

Abstract: A vehicle region with a roof section of a primary structure and with two luggage compartments. One of the luggage compartments comprises a detachable luggage compartment flap and a luggage compartment top, which forms the upper boundary of a part of a luggage space. A detachable fastening device can rotatably fasten the luggage compartment flap on the luggage compartment. A front edge of the luggage compartment top is at a distance from an end point in an intermediate space above a luggage compartment, to which end point a side of a ceiling panel is movable, the distance being greater than or equal to a width of the ceiling panel. Methods for installing and removing a ceiling panel above two luggage compartments are provided, wherein the ceiling panel is guided at least partially through a luggage space of a luggage compartment when the luggage compartment flap has been removed.

Abstract: A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.

Abstract: A wing for an aircraft, including a main wing, and a leading edge high lift assembly including a high lift body, and a connection assembly connecting the high lift body to the main wing such that the high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes a first connection element mounted to the high lift body and movably mounted to the main wing. The connection assembly includes a second connection element mounted to the high lift body spaced apart from the first connection element in a span direction, and movably mounted to the main wing. The connection assembly includes an additional support device arranged spaced apart from the first and second connection elements and configured to support the high lift body at the main wing against movement or deformation of the high lift body relative to the main wing.

Abstract: A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to a first connection element. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to a second connection element. The first output section includes a first output wheel and the second output section includes a second output wheel.

Abstract: A component made of a fiber-reinforced plastic, having a first surface portion, a second surface portion and a transition portion, which is enclosed by the first surface portion and the second surface portion, wherein surface tangents to the first surface portion and the second surface portion are not parallel, at least in regions adjacent to the transition portion. The transition portion has a curvature adjoining the adjacent surface portions in a tangentially constant manner, wherein an arrangement of at least two layers made of a fiber-reinforced plastic extends from the first surface portion, over the transition portion, onto the second surface portion, and fibers at least of one of the layers run with an unchanging orientation on the first surface portion and the second surface portion and, on the transition portion, run in a laterally offset, inflected or curved manner along the running direction.

Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) surrounding a plenum (7). The leading edge panel (3) has a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97). The outer wall element (23) includes micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25). The inner wall element (21) includes openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The outer wall element (23) extends from the first attachment end (17) to the second attachment end (19).

Abstract: An anticorrosion coating and an article coated with an anticorrosion coating, especially for use in an aircraft, and a method of producing a coated article and a vehicle, especially an aircraft, including an anticorrosion coating or at least one such coated article. An anticorrosion coating includes an aluminum alloy having 0.03-0.5% by weight of tin. A coated article produced at least partly from a material and having at least partly been coated with the anticorrosion coating including an aluminum alloy having 0.03-0.5% by weight of tin. A method of producing the anticorrosion coating is also disclosed.

Abstract: A wing for an aircraft is disclosed including a main wing, a leading edge high lift assembly having a leading edge high lift body, and a connection assembly movably connecting the leading edge high lift body to the main wing, wherein the connection assembly includes a drive system that is mounted to the main wing and connected to the leading edge high lift body for driving the leading edge high lift body between the retracted position and the extended position. The drive system includes a first drive unit and a second drive unit, the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section coupled to a first connection element and including a first output wheel. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section coupled to a second connection element and including a second output wheel.

Abstract: A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to the high lift body. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to the high lift body.

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Abstract: An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

Abstract: A fastening system including a structure holding element fastenable to a structural component. The fastening system includes a component holding element fastenable to a component to be fastened and movable relative to the structure holding element between first and second operating positions. A first lever element is connected to the structure holding element to be rotatable about a first rotation axis and is connected to the component holding element to be rotatable about a second rotation axis. The fastening system includes a connection element, connected to the component holding element to be rotatable about a third rotation axis and connected to the structure holding element to be displaceable in translation relative to the structure holding element, such that the second rotation axis, when the component holding element is transferred from its first into its second operating position, is displaced in a plane extending perpendicularly to the second rotation axis.

Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

Abstract: A table device for a vehicle cabin, in particular for a passenger cabin of an aircraft. The table device includes an active surface which is coated with at least one active material that is photoactive and antimicrobial. The table device furthermore includes an irradiation device, which is configured to irradiate the active surface with light. A passenger seat or a vehicle cabin may incorporate such a table device.