Abstract: An electronics installation system, especially for an aircraft or spacecraft, includes at least one mechanical installation structure having a plurality of installation slots each configured to receive an electronic module and at least one wiring configuration slot configured to receive a wiring configuration module, and a connection matrix comprising a plurality of data connections, wherein at least one data connection is provided between each one of the installation slots and at least one wiring configuration slot.

Abstract: A method of signaling speech signal related text messages on board an aircraft, a computer program product for carrying out such a method, an apparatus for signaling speech signal related text messages on board an aircraft, and an aircraft comprising such an apparatus. A method embodiment comprises: providing a speech signal related to an announcement to passengers of an aircraft; obtaining a text message containing text corresponding to spoken words of the speech signal; and signaling the text message to one or more devices on board the aircraft.

Abstract: An air conduction part for conducting a compressible medium, which part has a cross section through which the medium passes in a flow direction of the medium when the air conduction part is used, which flow direction approximately corresponds to a longitudinal axis of the air conduction part, the air conduction part including at least one wall arrangement that laterally defines the cross section of the air conduction part and conducts the medium. The wall arrangement are provided with at least one shell and with at least one damping device that removes sound energy from the medium, and the shell and the damping device are integrally interconnected so that, with a justifiable amount of outlay, the resulting air conduction parts effectively damp sound and the transport direction of the medium and/or the cross section of the air conduction part may change.

Abstract: An aircraft interior fitting component system comprising an aircraft interior fitting component, a support element attached to the aircraft interior fitting component, and an aircraft primary structure component. The support element is dimensioned in such a way and is attached to the aircraft interior fitting component in such a position that, in an assembled state of the aircraft interior fitting component in an aircraft, it is supported on the aircraft primary structure component at least when a predetermined load acts on the aircraft interior fitting component along the x-axis of the aircraft in flight direction.

Abstract: An aircraft air conditioning system including an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.

Abstract: An aircraft cabin arrangement is disclosed which extends in a rectilinear manner along a cabin axis, having a ceiling trim arrangement which delimits the cabin interior upwardly from the cabin axis, wherein the ceiling trim arrangement has a first, a second and a third row of ceiling trim elements, wherein the rows are arranged one immediately after another in the direction of extent of the cabin axis, wherein the rows have a central ceiling trim element and lateral ceiling trim elements, wherein the lateral ceiling trim elements of a row immediately adjoin the central ceiling trim element of the row in a laterally adjacent manner on both sides, perpendicularly to the cabin axis, wherein the lateral ceiling trim elements of the second row have one or more lighting sources, wherein the axial lengths of the ceiling trim elements of the first and the third row are different.

Abstract: A self-perforating spacer has a first part and a second part, the first part including a through-seat, the first and second parts being designed to be assembled together and the self-perforating spacer including a cutting system that cuts when the self-perforating spacer is assembled. A method for assembling a self-perforating spacer on an insulation blanket and an insulation blanket fitted with at least one self-perforating spacer is also described.

Abstract: A rotary joint includes a socket rod having a socket rod flange with an at least partly spheroid concave bearing surface at a first end, a housing nut encircling the socket rod and having a threaded wrenching head, and a ball rod having an at least partly spheroid convex bearing surface and threaded side walls around the bearing surface. The diameter of the threaded side walls of the ball rod corresponds to a diameter of the threaded wrenching head of the housing nut.

Abstract: A device for separating waste includes a tank having a closed internal chamber, the device being provided with an inlet opening and an outlet opening that can be connected to a suction system. The internal chamber of the tank is provided with a magnetic filter making it possible to attract and retain ferromagnetic waste likely to be entrained by the suction system into the tank, with a grating placed between the filter and the base of the tank, with a fluid discharge system at the level of its base. The device which is intended to be connected to a suction system makes it possible to retain and recover, sorted, the waste sucked in by said system and prevent the latter from polluting the pipelines thereof until they are blocked.

Abstract: A method for producing a fiber composite component assembly having at least first and second plate-shaped composite structures made from synthetic resin embedded fibers, the at least first and second fiber composite components having a plurality of partial regions not containing synthetic resin is described. The method includes positioning the at least first and second fiber composite components, the partial regions having been brought to flush conformity with each other, bonding the at least first and second positioned fiber composite components by the adhesive layer arranged in between, placing mechanical reinforcement means through the partial regions, infusing the dry partial regions with synthetic resin, and curing the synthetic resin placed in the partial regions.

Abstract: A mixing device that is particularly suitable for use in an aircraft air-conditioning system comprising a cold air supply line adapted to supply cold air to the mixing device. A first recirculation air supply line is adapted to supply recirculation air to the mixing device. A mixing chamber is connected to the cold air supply line and the first recirculation air supply line and is adapted to supply the cold air supplied to the mixing device via the cold air supply line with the recirculation air supplied to the mixing device via the first recirculation air supply line. The first recirculation air supply line has a heat transfer portion which is thermoconductively connected to an area of a wall delimiting the mixing chamber that is at risk of icing.

Abstract: An aircraft antenna assembly has a structural section of an aircraft, an antenna element, a cover transparent to radio waves, and a structural element. The structural section has an assembly of interconnected elongate longitudinal and transverse reinforcing elements and an outer skin arranged on one side of the assembly and secured on the reinforcing elements. A surface of the outer skin facing away from the elements forms an outer surface of the structural section. An opening closed by the cover, is formed in the outer skin. In the region of the opening, at least one of the reinforcing elements has a gap, in which the structural element is arranged and which divides the respective reinforcing element into two sections on opposite sides of the gap. The antenna element is arranged in the region of the opening on the opposite side of the outer skin from the outer surface.

Abstract: An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.

Abstract: An aircraft luggage system comprising a luggage compartment which comprises an upper side directed towards a ceiling of an aircraft when the luggage compartment is assembled in the aircraft, a lower side directed towards a floor of the aircraft, a rear side directed towards an outer contour of the aircraft, and two side faces connect the upper side to the lower side. The lower side of the luggage compartment is rigidly connected to the side faces and the rear side of the luggage compartment. A flap, movable between a closed position and an open position, is configured to make an inner space of the luggage compartment accessible or to close it. At least one additional luggage compartment is arranged adjacent to at least one of the upper side and the lower side of the luggage compartment.

Abstract: Method and system of simple, precise, rapid and automatic control to verify fit between a manufactured device and its digital mock-up modelling it beforehand. The system includes a scanner configured to produce a three-dimensional cloud of points representative of the device, as well as a processor and a memory configured to superpose the cloud of points on the digital mock-up, coordinate the cloud of points with polychrome images captured during the scanning of the device and stored in a memory, disperse the cloud of points into several sets of points, each set of points corresponding to an object identified in the polychrome images, establish a correspondence between the sets of points and nodes of a treelike structure identifying the digital mock-up, and evaluate a fit between the cloud of points and the digital mock-up by analyzing the correspondence between the sets of points and the nodes of the treelike structure.

Abstract: A seat track cover for a passenger seat of an aircraft is positionable on a seat track. The seat track cover is mechanically coupled at a first end to a seat leg structure of the passenger seat via a pivot joint. The seat track cover is arranged substantially parallel to the seat track and takes up a covering position which covers a seat track located therebeneath when the passenger seat is in its working position. The seat track cover takes up a stowed position in a second state, wherein, in the stowed position, the seat track cover is pivotable out of the parallel plane with respect to the seat track via a pivoting movement about the pivot of the pivot joint. The transition from the covering position to the stowed position takes place via the pivoting movement about the first end of the seat track cover.

Abstract: A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.

Abstract: A cover panel for a core panel of a structural aircraft component includes a protection cover having an outer shape corresponding to the outer shape of the core panel and including at least one cutout aperture, and at least one fabric panel mounted to the protection cover and covering the at least one cutout aperture.

Abstract: A mobile monitoring device including a data signal interface for coupling to a data line arranged in an aircraft and carrying one or more sensor signals, such that, in operation, the data signal interface branches off and receives as input signal part of the energy of the sensor signals carried on the data line such that the input signal is characteristic of the one or more sensor signals, and provide an output signal characteristic of the input signal. The mobile monitoring device further includes a wireless communication interface connected to the data signal interface for receiving the output signal and adapted to wirelessly transmit the output signal to a remote location. The present disclosure further relates to a system including an aircraft and the mobile monitoring device, and to a method of collecting sensor measurement data from a plurality of sensors of an aircraft using the mobile monitoring device.

Abstract: A passenger seat system for a cabin of a means of transportation includes: a passenger seat having a seat frame having a holding section and a plurality of supporting elements for coupling to a floor; and, a slide device spaced apart from the holding section and having a base and a retaining device, to be detachably fastened to the base and be coupled to a supporting element. The base has a contact surface for laying onto a cabin seat rail, a locking device for locking the base on the seat rail, and a holding device for releasably holding the retaining device. The slide device is designed to lock the retaining device on the holding device selectively in a first or a second position or to release the retaining device and, when the retaining device is released, to permit motion of the retaining device between the first and the second positions.