Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

Abstract: A fastening system includes a first fastening element attachable to a structure and which has a base portion for plugging through a structural opening, a second fastening element, and a plastically deformable funnel element. The funnel element has a funnel-like basic shape with a funnel opening. The second fastening element can be introduced through the funnel opening into a receiving opening of the base portion and fastened therein and has a collar which faces away from the receiving opening and which is larger than the funnel opening. The funnel element is designed to be deformed from the funnel-like basic shape into a flat, disk-like final shape by the collar of the second fastening element during the fastening of the second fastening element.

Abstract: A cryogenic fluid pressure vessel for an aircraft, having: a first wall layer, which contains carbon fiber-reinforced plastic, having an inner contact surface for the contact with a pressurized cryogenic fluid to be accommodated inside the cryogenic fluid pressure vessel; a second wall layer, which is arranged on an outer surface of the first wall layer and has a thermal barrier; a closable inlet/outlet opening for cryogenic fluid, which extends through the first and the second wall layer; and a structural insert integrated in the first and the second wall layer, which has a fastening connecting piece located on the outside of the cryogenic fluid pressure vessel for mechanically coupling the cryogenic fluid pressure vessel with external structures; wherein the cryogenic fluid pressure vessel forms an essentially cylindrical main body. Furthermore, the present invention provides an aircraft having such a cryogenic fluid pressure vessel.

Abstract: Film for the repair of aircraft components made of fiber-reinforced thermoplastic including an embossed film made of polyimide and a coating made of an electrically conductive material.

Abstract: A leading edge assembly for an aircraft wing. The leading edge assembly includes a housing configured to be connectable to a fixed wing section of the wing, the housing formed with a first opening connecting an exterior of the housing with an interior of the housing, an actuating element movably connected to the housing, such that the actuating element is movable between a first position and at least one second position. The actuating element extends through the first opening and includes a first section arranged in the interior of the housing and a second section arranged at the exterior of the housing. The actuating element is configured to be connectable to a high lift device.

Abstract: A method for producing a component with a surface that is suitable for plastic welding or adhesive bonding of two parts is provided. As a preparation step prior to joining, a filler sheet comprising a thermoplastic material or adhesive is arranged on a first surface of a first component and a structuring tool is arranged on the filler sheet. Mechanical force is applied to the structuring tool and heat is applied to the filler sheet such that the filler sheet is attached to the first surface of the first component and such that the structuring tool is partially embedded in the filler sheet. The structuring tool is subsequently removed from the filler sheet to produce a plurality of protrusions in the outer surface of the filler sheet. After surface structuring the first and second components are joined using any type of welding technique or joined using of adhesive bonding.

Abstract: A system for positioning vehicle components relative to each other on a floor to prepare an assembly. A plurality of carriers receive a vehicle component. A plurality of positioning tables have a lower portions which can be fixed to the floor and a upper portions which receive a carrier. A location device having at least one base and mobile units moveable relative to the base. At some of the positioning tables moves the respective upper portion along at least two movement axes relative to the respective lower portion to position a carrier located thereon. A transport device guides the carriers from an external position to a positioning table and to place them on the upper portion. The location device determines the positions of the respective mobile units relative to the at least one base. A position control unit controls a movement of the upper portions to a predetermined target position.

Abstract: A fastening system for suspended installation of stowage compartments, in particular in aircraft, includes a first fastening element, which fastens on a supporting structure, a second fastening element, which fastens on a stowage compartment, and a connecting arrangement, configured for surface-area fastening on the first fastening element. The connecting arrangement and the second fastening element each include a supporting eyelet for accommodating a fastening bolt, to fasten the connecting arrangement on the second fastening element.

Abstract: A lavatory door system for a vehicle, in particular an aircraft, with a lavatory door; a pneumatic actuator configured to open and close the lavatory door based on a differential pressure, wherein the pneumatic actuator is coupled to a vacuum toilet system of the vehicle to generate the differential pressure; and an operating interface configured to receive a user control operation and to selectively release the differential pressure from the vacuum toilet system for operation of the pneumatic actuator based on the received user control operation.

Abstract: A wing (3) for an aircraft (1) including a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5). The trailing edge high lift assembly (9) includes a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5). The connection assembly (13) includes an actuator unit (35) moving the flap (11) between a retracted position and at least one extended position. The flap (11) includes a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) pivotable about a pivot axis (31).

Abstract: The disclosure concerns a wing for an aircraft including a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly having a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position. The connection assembly includes an actuator unit for moving the flap between the retracted position and the at least one extended position. The flap includes a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis.

Abstract: In order to improve liquid hydrogen storage on aircraft, a liquid hydrogen tank is integrated into the fuselage of the aircraft. At least one portion of the tank wall is formed by specially adapted tank skin panels and/or a pressure bulkhead. The parts forming the tank wall are strengthened to contain a tank pressure of about 3 bar.

Abstract: A power control unit configured to supply hydraulic pressure and mechanical torque. To this end, the power control unit includes an electric motor coupled to a differential output transmission and a hydraulic pump. A switchable transmission device allows the torque of the motor to be redirected either to the output transmission, e.g., to drive high-lift devices, or to the hydraulic pump, e.g., to extend or retract landing gears.

Abstract: A method for ultrasonic inspection of composite parts includes providing a composite part to be inspected with a plurality of layers, determining the runtime and/or attenuation of an ultrasonic signal propagating through the composite part to be inspected, providing the runtime and/or attenuation of the ultrasonic signal propagating through a reference composite part, subtracting the runtime and/or attenuation of the ultrasonic signal in the reference composite part from the runtime and/or attenuation of the ultrasonic signal in the composite part to be inspected, or vice versa, and determining from the result of the subtraction one or more missing and/or additional layers in the inspected composite part. The difference of the runtime and/or attenuation of the ultrasonic signal in the inspected composite part relative to the reference composite part, and/or the difference of the thickness between the composite part and the reference part, is/are visualized.

Abstract: A system for producing a component or semifinished product with a fibre-reinforced foam core, includes a substrate on which the foam core having a first main surface and an opposite second main surface is to be laid; a sewing device having a needle configured to be moved at least linearly; a fibre supply device for three-dimensional supply of a fibre; and a coating device. The sewing device is configured to position the needle at the first main surface and to pierce the foam core, such that a needle tip penetrates through the first main surface and then through the second main surface. The fibre supply device is configured to position a reinforcing fibre such that the reinforcing fibre is hooked into the needle tip. The coating device is configured to coat a reinforcing fibre hooked into the needle tip with resin immediately before the reinforcing fibre enters the foam core.

Abstract: A method for removing a two-part connector in a workpiece arrangement includes providing a workpiece arrangement having first and second surfaces and having a hole connecting the first surface to the second surface. A connector is fastened in the hole, which connector has a bolt extending along a central axis and a sleeve fastened on the bolt. The bolt has a head portion and a shank portion with retaining grooves. The sleeve is fastened to the bolt on the side of the second surface such that the inner surface thereof engages with the retaining grooves and prevents a relative movement of bolt and sleeve parallel to the central axis. The sleeve has an outside diameter which is greater than the diameter of the hole in the workpiece arrangement. The sleeve is cut and or the bolt, and the connector is removed from the hole.

Abstract: A method for operating an on-board water supply and distribution system of an aircraft for supplying water includes a central water tank, first consumer assemblies with buffer tanks each including a heater to heat up water in the buffer tank to a disinfection temperature, pump having upstream and downstream sides to operate in supply and reverse modes, and high-pressure conduit system. The central water tank connects to the pump's upstream side. The conduit system connects the downstream side with a first consumer assembly. The method includes operating the pump in supply mode where water from the central tank goes to a first consumer assembly to fill a buffer tank, operating a buffer tank heater so water heats to a predetermined disinfection temperature, and operating the pump in reverse mode so heated water passes through a part of the conduit system and the upstream side of the pump.

Abstract: A method for applying a corrosion protection layer to a surface to be protected of a component including providing the corrosion protection layer having a first surface and a second surface arranged opposite this, laying the first surface of the corrosion protection layer on a bottom face of a mold, laying the surface to be protected of the component on the second surface of the corrosion protection layer so as to enclose a layer of hardenable sealing compound, closing the mold by applying a bend-flexible cover so as to enclose the corrosion protection layer and the component, evacuating the mold so that the cover presses the component in the direction of the corrosion protection layer, and removing the vacuum and the cover after hardening of the sealing compound.

Abstract: A buffer for storing liquid at a consumer pressure includes a storage volume for holding a liquid and a gas. The storage volume may be separated by a partition element into a liquid compartment for holding the liquid and a gas compartment for holding the gas. A pressurizer is configured for increasing the pressure of gas in the storage volume to an operating pressure when liquid is or has been drained from the storage volume. A ventilator reduces the pressure of gas in the storage volume back to the operating pressure when the storage volume is filled with liquid. A water supply system for an aircraft including the buffer and an aircraft including such a water supply system are disclosed.

Abstract: An aircraft wing includes a main wing and a high lift assembly having a high lift body, and a connection assembly movably connecting the high lift body to the main wing to be movable between a retracted and an extended position, and having an elongate track extending along a longitudinal axis between a first end and a second end. The first end of the track is mounted to the high lift body. The track is mounted to the main wing via a roller bearing to be movable along the longitudinal axis. The roller bearing includes a first and a second roller mounted to at least one of the main wing and the track via first and second eccentric connector assembly, respectively. The first and second eccentric connector assemblies are configured to be engaged simultaneously by a single alignment member for synchronous rigging of the first and second rollers.