Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes at least one hydrogen supply means, an air channel having an inlet and an outlet, an air cooled fuel cell unit couplable with the hydrogen supply means and arranged inside the air channel and at least one catalytic converter couplable with the hydrogen supply means and arranged between the fuel cell unit and the outlet of the air channel inside the air channel. The air cooled fuel cell unit is adapted for conducting a fuel cell process under consumption of air flowing from the inlet of the air channel through the air cooled fuel cell unit and hydrogen from the hydrogen supply means. At least one catalytic converter is adapted for producing water and oxygen depleted air under consumption of hydrogen from the at least one hydrogen supply means and air.

Abstract: An aircraft ground support equipment, GSE, unit for externally accessing video data from an aircraft video surveillance system, AVSS. The GSE unit constitutes a back-up AC power supply for the aircraft's AVSS and comprises a power output connector for connecting a power cable to a ground connection panel on the outside of the aircraft. AC power is supplied either by a rechargeable battery through a converter, or by mains power plugged into the GSE unit. A power source selection switch is switched to route either battery power or external power to the aircraft dependent on factors including battery status, presence of power at the external power connector and presence of power in the aircraft. Video data from the AVSS can thus be streamed out, even in the absence of aircraft power, for example to a portable personal computer.

Abstract: A system for generating a moving image in an aircraft, includes a multiplicity of LEDs, a signal input unit, into which image information is fed, a signal output unit coupled to the multiplicity of LEDs and configured for transmitting the image information to the multiplicity of LEDs, and a gyroscopic sensor for acquiring a spatial position of the aircraft, wherein the LEDs are arranged in the form of a grid on an aircraft interior wall, such that the image is a schematic reproduction of the image information and the signal output unit is coupled to the gyroscopic sensor in such a way that the position of the image is matched to the spatial position of the aircraft, such that the image forms an artificial horizon for a viewer.

Abstract: A virtual window device, particularly for use in an airplane, includes a bezel, or a frame, with a display arranged within the bezel, or within the frame; a distance sensor unit configured to produce at least one first distance signal indicating a first distance to an object; a first camera unit configured to capture a live video of a real scene; and a computing unit configured to select, based at least on the at least one first distance signal, a section of the live video of the real scene captured by the first camera unit; wherein the computing unit is further configured to control the display to display the selected section.

Abstract: A rotational joint (101) that rotatably couples a wing tip device (4) to a fixed wing (3), and includes an outer race (8) and an inner race (9), a rotational drive member (70) and the race that is rotationally fixed relative to the wing tip device (4) each being provided with a coupling section (110, 111, 114), the coupling sections coupled to each other by a coupling member (119), that is received in a bore (112, 113) in one of the coupling sections, such that rotation of the drive member (70) rotates the race that is rotationally fixed relative to the wing tip device, to rotate the wing tip device (4) from one configuration to the other, wherein the coupling member (119) is mounted in the bore such that it is movable radially within the bore.

Abstract: A cable harness test system includes a cable tester that has a microcomputer and a multiplicity of first test point connections for connecting first ends of a multiplicity of electrical lines of a cable harness and is designed to feed line test signals into the multiplicity of electrical lines of the cable harness at the first test point connections, and also a multiplicity of interface simulation devices that each have a multiplicity of second test point connections for connecting second ends of the multiplicity of electrical lines of the cable harness and are each designed to return line test signals received from the cable tester at the second test point connections to the cable tester by the multiplicity of electrical lines of the cable harness.

Abstract: An aircraft ceiling liner element comprises a load-bearing carrier platform, configured to form a part of an aircraft ceiling liner, and a mounting mounted on the carrier platform, connectable to a primary structure of the aircraft. An electrical connection mounted on the carrier platform is connectable to an electrical supply network of the aircraft. Furthermore, the aircraft ceiling liner element comprises a mechanical interface mounted on the carrier platform, configured to attach various interchangeable modular units detachably and in a load-transferring manner to the carrier platform, and an electrical interface mounted on the carrier platform, which interface is configured to create an electrical connection between the modular unit and the carrier platform.

Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface, and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: A cabin monument for an aircraft. The cabin monument has a framework with a base frame and a frame structure connected to the base frame, and side walls fastened to the frame structure. By fastening the side walls to the structural struts of the frame structure, a mechanical load acting on the cabin monument is distributed between the framework and the side walls.

Abstract: An aircraft bipolar high-voltage network includes a DC voltage converter comprising two unipolar input connections, two bipolar output connections and a reference potential connection, and at least one unipolar device having two electrical connections which are each coupled to one of the two unipolar input connections. The DC voltage converter has a first DC voltage converter module coupled to a first of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a first of the bipolar output connections via a module output connection, and a second DC voltage converter module coupled to a second of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a second of the bipolar output connections via a module output connection.

Abstract: A vehicle cabin seat rail system includes a seat rail having a top side having a plurality of raster openings and mechanically couplable with a cabin floor, a plurality of holding devices positionable on the top side, each being selectively engageable with at least one first raster opening or at least one second raster opening for arresting the holding device and configured for holding an object on the seat rail, and a plurality of marking devices couplable with the seat rail, and configured for optically or mechanically indicating approaching of a first position on the seat rail corresponding to the first raster opening of a respective holding device and of a second position of the same holding device corresponding to the second raster opening, in relation to another object arrested on the seat rail, to prevent an arresting of the holding device on the seat rail on other positions.

Abstract: A method for producing a connecting device for connecting films with conductor tracks includes the steps of laying a first film with conductor tracks onto a forming die, applying a first lower shell of a plastic material onto a first end portion of the forming die, producing a cut-out and shifting the first film so that the cut-out lies completely on the first lower shell, applying upper conductor tracks of a conductive material onto the first lower shell so that the upper conductor tracks overlap with the conductor tracks of the first film, and applying a first upper shell of a plastic material onto the first lower shell so that the first film, the first lower shell and the first upper shell connect together by substance bonding to form a first connector. In this way, an integral connector can be provided on each film.

Abstract: A wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19?), and an actuating arrangement having an actuator (21) which is coupled to the base section (7) and the tip section (13) and which is operable to effect a pivotal movement of the tip section (13) relative to the base section (7) between a stowed position and a deployed position.

Abstract: A fuel cell system includes a first fuel cell unit having a first fuel cell and a second fuel cell, a second fuel cell unit having a third fuel cell and a fourth fuel cell, a hydrogen tank coupled to all fuel cells, an oxygen supply unit and an air inlet. Oxidant inlets of the first fuel cell and the fourth fuel cell are couplable with the air inlet. Oxidant inlets of the second fuel cell and the third fuel cell are couplable with the oxidant supply unit couplable with at least one of the oxygen supply unit and the air inlet. Exhaust outlets of the first and fourth fuel cells are couplable with an inert gas outlet. Exhaust outlets of the second and third fuel cells are coupled with an exhaust switching unit couplable with the inert gas outlet and a water outlet.

Abstract: A fastening system for passenger seats in a vehicle cabin has two or more guide rails to be integrated into or onto a cabin floor, and a plurality of slides, to be brought into engagement with the guide rails and having a flange for connection to a passenger seat in order to retain the passenger seat on a guide rail. Each guide rail has a profile cross section, perpendicularly to a main axis of extent, having a base region and a supporting region. Each slide has a cavity of complementary design with the profile cross section. The guide rails have a plurality of transverse openings spaced apart from one another between the base region and the supporting region. At least one slide has a displaceably mounted retaining body which, when the slide is in engagement with the guide rail, can be brought into engagement with one of the transverse openings.

Abstract: A flow body of an aircraft includes: a flow surface exposed to an airstream during flight of the aircraft, the flow surface generating at least one region of turbulent airflow during flight of the aircraft, at least one perforated area including a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings, and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold, the second end including a suction opening and being arranged in the at least one region of turbulent airflow, wherein the suction opening is adapted for inducing a suction force in the at least one suction duct when the flow surface is exposed to an airstream during flight, thereby inducing a flow of air from through the plurality of openings.

Abstract: A network for an aircraft including a data line and network access devices, a first interface and at least one second interface and connected to the data line via the first interface. Identifiers are assigned to the second interfaces in pairs. The access devices receive and/or transmit data in first data frames having a fixed format and first portion and second portions. The network access devices transmit second data frames and, for each second interface, a sequence of third data frames received on the second interfaces, the network access device including a first processing unit to insert the second data frames in the first portion of the first data frames, split each third data frame into fragment frames, including a part of the respective third data frame and reassembly information allowing regeneration of the third data frame from the fragment frames, and insert the fragment frames into the second portions.

Abstract: A vortex generator arrangement for an aircraft, a flow control system and an aircraft comprising such vortex generator arrangement. The arrangement includes a surface portion facing a first region of space to constitute a flow surface, a vortex generating element, an element support structure connected to the element, a mounting structure. The element support structure and the element together are rotatable between first and second positions and a biasing device, retainer and release are provided. The rotational axis extends transversely with respect to the surface portion. The projection of the element onto a projection plane is smaller in the first rotational position than in the second rotational position, the projection plane extending perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to the extension of the tangent plane.

Abstract: A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body configured to rotate around an axis parallel to the pintle axis of the hooking pintle. The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch in hooking engagement with the hooking pintle and to retain the door latch in a direction perpendicular to the door body in an overcenter position.

Abstract: An additive layer manufacturing method is disclosed for producing a three-dimensional object and a corresponding object. Layers of powder material are applied to a carrier and each layer is irradiated with a laser beam or a particle beam only in areas of the layer corresponding to the three-dimensional object to be produced. Irradiation occurs so the powder material in the corresponding areas is locally melted or sintered. An elongate portion of the object is constructed so longitudinal channels extend at an angle of more than 45° to the direction of the force of gravity, and along its entire length the longitudinal channels are formed so that in cross section perpendicular to the direction of extension of the elongate portion the minimum distance to the outer surface of the elongate portion is not smaller than the minimum distance to the closest neighbouring longitudinal channel or the closest neighbouring longitudinal channels.