Abstract: In a method for manufacturing a sandwich component having a first and a second flat side, in a pre-assembly state all components of the sandwich component in relation to one another are placed in a nominal position: at least one shape-imparting structural layer and a conductor layer having an electrical conductor, and are connected in an assembly step with an adhesive, wherein in the pre-assembly state on both sides of the conductor layer two barrier layers which are vapor-tight are placed as further components and interconnected in such a manner that said two barrier layers enclose the conductor in a vapor-tight manner.

Abstract: The present application relates to a hybrid component and a method for producing the same. The proposed hybrid component comprises a basic element (2) having at least one portion which is formed as a laminate (3) from a plastics foam and a fiber composite plastic.

Abstract: A light-emitting composite arrangement for stationary arrangement in an interior of an aircraft is provided. The light-emitting composite arrangement has a base layer, a covering layer and a core portion at least partially provided between the base layer and the covering layer. The covering layer can be a prepreg layer. A lighting device is integrated in the core portion. The covering layer is cured with the lighting device integrated in the core portion.

Abstract: A particle separator comprises a pipeline that allows a fluid to flow in a curved direction of flow. The particle separator includes an inlet region, a curved deflection region, which in the direction of flow follows on from the inlet region, with an inside wall and an outside wall, and a delimitation body. The delimitation body at least in some sections extends between the inside wall and the outside wall in the interior of the deflection region and is curved in the same direction as the deflection region.

Abstract: In a method for manufacturing a sandwich component having a first and a second flat side, in a pre-assembly state all components of the sandwich component in relation to one another are placed in a nominal position: at least one shape-imparting structural layer and a conductor layer having an electrical conductor, and are connected in an assembly step with an adhesive, wherein in the pre-assembly state on both sides of the conductor layer two barrier layers which are vapour-tight are placed as further components and interconnected in such a manner that said two barrier layers enclose the conductor in a vapour-tight manner.

Abstract: A method for manufacturing a cladding element for a passenger cabin of a vehicle is provided. A first layer is introduced into a forming shell. A support layer is provided onto the first layer, such that the first layer extends beyond an edge of the support layer. An elastic material strip is provided onto a portion of the first layer hat extends beyond the support layer, such that the material strip is flush with the edge of the support layer. A second layer is provided onto the support layer, such that a portion of the second layer extends beyond the edge of the support layer and is superimposed on the material strip. The forming shell is closed and a pressure is exerted on the layer arrangement accommodated in the forming shell at a temperature between 50° C. to 100° C., to form a sandwich structure.

Abstract: A light-emitting composite arrangement 1 for stationary arrangement in an interior of an aircraft is proposed, comprising a base layer and a covering layer 2, 3, wherein the covering layer 3 is a prepreg layer, comprising a core portion 4, which is arranged, at least in some areas, between the base layer and the covering layer 2, 3, comprising at least one lighting device 5, which is integrated in the core portion 4, wherein the covering layer 3 is cured with the lighting device 5 ntegrated in the core portion 4.

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: A baggage compartment for an aircraft is provided. A housing and a baggage container of the compartment are mounted to each other to allow pivotable movement of the baggage container along a pivot axis. As a result, the baggage container is moveable from an open position into a closed position. The compartment has a pulling arrangement for transferring a pulling force to the baggage container to move the baggage container from the open position into the closed position. The compartment also has a drive arrangement for transferring the pulling force to the pulling arrangement. The drive arrangement has a linear drive and a sliding device.

Abstract: Aircraft panel 1 for an interior of an aircraft, wherein the aircraft panel 1 has a sandwich structure 2, wherein the sandwich structure 2 comprises a core section 4 and a covering section 3 as sandwich layers, wherein the covering section 3 comprises a prepreg layer 6 and wherein the aircraft panel 1 comprises at least one switching element 8 for activating at least one electrical device of the aircraft, wherein at least one switching element 8 is fixed in the covering section 3 by the prepreg layer 6.

Abstract: The present application relates to a hybrid component and a method for producing the same. The proposed hybrid component comprises a basic element (2) having at least one portion which is formed as a laminate (3) from a plastics foam and a fiber composite plastic.

Abstract: A fastening device for connecting two overhead storage compartment elements of an aircraft is provided. The overhead storage compartment elements have coupling elements on the sides of the overhead storage compartment elements to be connected. The coupling elements need to be aligned with one another without being subjected to loading. A connecting plate is arranged on a first fastening element, 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 and does not interfere when the bulky overhead storage compartment element is handled before attaching to the cabin ceiling.

Abstract: The invention relates to a sound-attenuating device for separating off spaces in an aircraft, wherein the device (11) has a screening element (1) which is connected to a supporting means (4) such that it can be moved from a closed state to an open state, and which is designed to at least partially close an opening (12), wherein the screening element (1) comprises a first layer (6) having a sound-reflecting characteristic and a compressible second layer (7) having a sound-absorbing characteristic, which layers are arranged between a first cover layer (8) and a second cover layer (9), wherein the first layer (6), the second layer (7), the first cover layer (8) and the second cover layer (9) are stitched so as to form longitudinal seams (2), along which the screening element (1) can be folded.

Abstract: Baggage compartment 1 for an aircraft, wherein the baggage compartment 1 comprises a housing 2 and a baggage holder 3, wherein the baggage holder 3 is swivel-mounted about a swivel axis A in the housing 2, wherein, the swivel axis A intersects, in its longitudinal extent, a holder side wall 32 of the baggage holder 3 and/or a housing side wall 21 of the housing 2, wherein the baggage holder 3 can be moved from a closed position G into an open position Ö with a first swivel movement S1 and the baggage compartment 1 is opened and wherein the baggage holder 3 can be moved from the open position Ö into the closed position G with a second swivel movement S2 and the baggage compartment 1 is closed, wherein the baggage compartment 1 comprises a drive device 6 having at least one drive motor 9, wherein the drive device 6 is designed to drive the baggage holder 3 during the first and/or second swivel movement S1; S2 and to open or close the baggage compartment 1, wherein the drive device 6 is connected to the holder s

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: Luggage storage compartment for an aircraft, comprising a housing and a luggage container being mounted pivotably in the housing about a pivot axis A, and being transferrable with a first pivoting motion S1 from a closed position G into an open position Ö and the luggage storage compartment being opened, and being transferrable with a second pivoting motion S2 from the open position Ö into the closed position G and the luggage storage compartment being closed, the luggage storage compartment having a pivoting apparatus, comprising a cable winding device with a winding roll and with a winding medium, the pivoting apparatus comprising a drive device with a drive motor for driving the winding roll, an axis of rotation D of the winding roll running in the same direction as and/or parallel to the pivot axis A of the luggage container.

Abstract: The invention relates to a method for the manufacturing of a cladding element for a passenger cabin of a vehicle, in particular of a land vehicle, an aircraft, or a watercraft, comprising the following steps: introducing a first layer, which is provided with first fibres and impregnated with a resin, into a forming shell, layering of a support layer, which is sheet-like and reinforced with second fibres, onto the first layer, such that the first layer extends beyond at least one edge of the support layer, layering of an elastic material strip onto that portion of the first layer that extends beyond the support layer, such that the material strip bears flushly against the edge of the support layer, layering of a second layer, which is provided with the first fibres and impregnated with the resin, onto the support layer, such that a portion of the second layer extends beyond the edge and lies over the material strip, and closing the forming shell and exerting a pressure on the layer arrangement, which is ac

Abstract: A baggage compartment for an aircraft is provided. The compartment has a housing and a baggage holder swivel-mounted in the housing. The baggage holder is moveable from a closed position into an open position with a first swivel movement to open the baggage. The baggage holder is moveable from the open position into the closed position with a second swivel movement to close the baggage. The compartment also has a swiveling device for moving the baggage holder into the open or closed position by performing the first or second swivel movement.

Abstract: An overhead luggage compartment for a vehicle cabin is provided. The compartment has a ledge pivotably held about a pivot axis in a housing half-shell. The ledge is connected to the housing half-shell through a damper for damping a pivoting movement. One end of the camper is attached to a ledge side wall. The other end of a damper is attached to a damper fastening element. The damper fastening element is rotatably attached to the ledge side wall about the pivot axis. A damper mating fastening element corresponding to the damper fastening element is fixedly attached to a housing half-shell side wall opposing the ledge side wall. With an engagement of the damper fastening element in the damper mating fastening element, a connection, which is fixed in terms of rotation, is made between the damper fastening element and the damper mating fastening element.

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.