Abstract: A method for the connection of moulded parts, wherein a locking collar pin with locking grooves or with an external thread, is driven through the moulded parts and subsequently a locking collar is locked together with at least some of the locking grooves, or with threaded sections of the locking collar pin, by the application of radial pressure, or by means of a screwing operation. A connecting system with a locking ring pin, which has a punching section for purposes of punching through the moulded parts, and also locking grooves for purposes of active engagement with a locking ring; the latter extends over at least two adjacent locking grooves in the axial direction, or over at least two adjacent threads in the axial direction.

Abstract: An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise.

Abstract: A damping device, in particular for damping or avoiding pressure surges, such as pulses, in hydraulic supply circuits, preferably in the form of a silencer, having a damping housing (1) which surrounds a damping chamber and has at least one fluid inlet (35) and at least one fluid outlet (41) and a fluid receiving chamber which extends between the fluid inlet (35) and the fluid outlet (41), wherein, during operation of the device, a fluid flow crosses the damping chamber in a throughflow direction (11), coming from the fluid inlet (35) in the direction of the fluid outlet (41), and wherein at least parts of the fluid receiving chamber extend in at least one extent direction transversely with respect to the throughflow direction (11), is characterized in that more than one fluid receiving chamber is arranged one after the other in the throughflow direction (11) and in that the fluid receiving chamber which is first upstream and the fluid receiving chamber which is last downstream immediately adjoin the fluid in

Abstract: A wearable device that is wearable by a user and connectable with one or more aircraft related systems, a device system comprising a plurality of such wearable devices, and an aircraft comprising such a device system. The wearable device that is connectable to one or more aircraft related systems comprises a system interface via which the wearable device is connectable to one or more aircraft related systems, and a control unit configured to communicate with at least one of the one or more aircraft related systems via the system interface.

Abstract: A support rack configured for an aircraft including: a rectangular frame including four substantially straight segments and four feet, wherein upper surfaces of each of the substantially straight segments and the four feet are substantially aligned with a upper plane of the rectangular frame; a first set of attachment holes configured to attach at least one item of aviation electronic equipment, wherein the first set of holes are in the upper surfaces of the straight segments or the, and a second set of attachment holes configured to receive anchoring elements that anchor to a structure of the aircraft, wherein the second set of attachment holes are at a surface of the rack out of the substantially upper planar.

Abstract: A method for testing the fracture toughness of an adhesive joint to be formed between two components made of fiber-reinforced plastic, by forming a test joint between two sample elements and applying a tensile load onto this test joint until a pre-defined value is reached. One of these sample elements is formed by one of the components of the joint to be formed, and the tensile load acts on the other sample element.

Abstract: A floor system for a vehicle is provided. The floor system includes at least one floor panel having a top surface, a bottom surface and a first recess extending through the top surface, at least one primary coil device having at least one primary coil and a connection line, and at least one cover plate. The at least one primary coil device is positioned inside the first recess and the at least one cover plate is located in the recess above the at least one primary coil device so as to close the first recess flush with the top surface. It is possible to provide the at least one floor panel made from a carbon fiber reinforced material as it cannot electrically shield the at least one primary coil to a space above the top surface, when the at least one cover plate is made from a non-conductive material.

Abstract: An aircraft including a fuselage extending along a longitudinal axis and having a rear end pointing reward of the aircraft, a main gear connected to the fuselage in a main gear position with respect to the longitudinal axis, and an engine for propelling the aircraft provided outside of the fuselage and attached to the fuselage via an attachment device between the main gear position and the rear end, wherein the engine generates a repulsive air stream streaming in the reverse direction. A surface element is moveably connected to the attachment device. The surface element moves between a neutral position at which it does not deflect the repulsive air stream, and a deflected position at which it deflects the repulsive air stream to assist aircraft rotation during take-off.

Abstract: An aircraft fuselage includes at least one space arranged in the aircraft fuselage and at least one wall. The wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage underneath the space does not include burnthrough-resistant insulation. The space may be a cargo compartment of the aircraft or a passenger cabin, while the wall may be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly fairing). The design of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: In a method for processing a fiber compound structure, an unhardened fiber layer is arranged on a surface section of the fiber compound structure. A pressure cushion is arranged above the surface section. The pressure cushion has a pressure cap and a pressure-tight cap mat pressure-tightly connected to a circumferential border of the pressure cap such that the cap mat limits a pressure area together with the pressure cap. An overpressure in the pressure area is generated. The pressure cushion is pressed onto the fiber compound structure such that the overpressure presses the cap mat against the fiber layer while supporting the fiber compound structure on a side of the fiber compound structure that is opposed to the surface section.

Abstract: A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Abstract: A structural component includes a composite laminate built up of a plurality of layers of carbon fibres, wherein the layers of carbon fibres are oriented in different directions, wherein the carbon fibres are surrounded by a conductive polymer resin, wherein the carbon fibres of at least one of the layers comprise an electrically insulating coating, and wherein at least one of the coated carbon fibres extend through its respective layer to form an electrical connection between ends of the layer spaced apart from one another.

Abstract: The disclosure relates to a lighting unit for an aircraft interior having a floor with a baseplate fastenable to structure of the aircraft, and having a receiving region that faces away from the structure in a fastened state. An OLED light source having one or more OLEDs is arranged in the receiving region. The lighting unit also has a lens arranged on a side of the OLED light source facing away from the baseplate, and a frame mechanically retained in the receiving region by plug contacts such that the OLED light source and the lens are fastened in the receiving region. The plug contacts include electrical and mechanical contacts, wherein the OLEDs are supplied with electricity by at least one controllable driver, and wherein the contacts supply electricity to the OLED light source.

Abstract: A system for operating an aircraft door includes an operating handle having a lever and a grip, a slide arming means movable between a first position representing an armed state and a second position representing a disarmed state, a control unit coupled with the slide arming means, warning means arranged in the vicinity of the slide arming means and a sensor. The sensor is adapted for detecting the proximity of a hand of a user in a field around the grip, which field covers a distance of at least 10 cm and not exceeding 50 cm to the grip, and for producing a proximity signal representing the proximity of a hand of a person. The control unit is adapted for operating the warning means on receiving the proximity signal of the sensor to attention to the slide arming means when the slide arming means is in the first position.

Abstract: A rail system, in particular for assembling or fastening seats in an aircraft, includes an assembly rail, in particular a seat rail for assembling or fastening a seat, a first panel, in particular a first floor panel for arrangement next to and substantially in parallel with the assembly rail, and at least one cover element which is movable between a first position in or on the first panel and a second position for covering the assembly rail, wherein an upper surface of the at least one cover element in the second position is located substantially in a plane with a surface of the first panel.

Abstract: A divider element for an aircraft cabin is disclosed including a frame member forming a closed ring wherein the frame member may assume an expanded state and a collapsed state, wherein in the expanded state the frame member extends in a plane and defines a first area which is surrounded by the frame member and wherein in the collapsed state the frame member defines a second area which is surrounded by the frame member, the second area being smaller than the first area, and a flexible sheet member which is fixed to the frame member and dimensioned such that when the frame member is in the expanded state, it extends over the area defined by the frame member.

Abstract: A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.

Abstract: A combination comprises an aircraft wing trailing edge section and an adjustment body. The adjustment body comprises a tapered cross section in a local chord axis direction of the wing trailing edge section, a lower adjustment body surface connected to a top surface of the aircraft wing trailing edge section and a back-end surface having a height. The adjustment body is positioned such that the back-end surface is flush with the trailing edge of the aircraft wing trailing edge section. Attaching the adjustment body onto a top surface of the wing trailing edge section leads to compensation of an offset rolling moment due to unavoidable structural shape deviations of the aircraft and eliminates additional structural reinforcement requirements on the trailing edge compared to edge wedges mounted on the bottom surface of trailing edges. The trailing edge section may comprise a flap.

Abstract: A mixer assembly for an air-conditioning system comprising a recirculation air line, connectable to a vehicle region to be air-conditioned, to remove recirculation air from the region, and an air-conditioning air line, connectable to an air-conditioning unit to remove conditioned air from the air-conditioning unit. A first mixing region, for mixing the recirculation air with the conditioned air, is connected to the two air lines. A second mixing region, for mixing the first mixing region air with recirculation air, is connected to the recirculation air line and the first mixing region. Also, a first supply line is connected to the first mixing region to supply air from the first mixing region to a first partial region of the vehicle region, and a second supply line is connected to the second mixing region to supply air from the second mixing region to a second partial region of the vehicle region.

Abstract: A passenger seat arrangement comprises at least one first seat arranged at a first lower level, and at least one second seat arranged at a second elevated level. Each of the first and the second seats comprises a supporting surface for supporting a passenger which is movable between an upright seating position and a reclined lying position. At least one of the first and the second seats is constructed in such a manner that a movement of its supporting surface from the upright seating position into the reclined lying position results in an increase of a distance between the supporting surface of the first seat and the supporting surface of the second seat.