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: 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 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 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: 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 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 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 drive assembly for driving a movable flow body of an aircraft, includes: a power drive unit, a flight control computer, a first flex shaft connecting the power drive unit to an inboard drive station, a second flex shaft connecting the inboard drive station to an outboard drive station, a first actuator connected to the inboard drive station and being couplable with the movable flow body, a second actuator connected to the outboard drive station and being couplable with the movable flow body. The second actuator includes a redundant position feedback sensor. The power drive unit includes a power-off brake, wherein the position feedback sensor is configured to send a position feedback signal to the flight control computer, and the flight control computer is configured to control the power drive unit.

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.

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, such that the high lift body is movable between retracted and extended positions. The connection assembly includes an elongate track extending along a longitudinal axis between first and second ends and has an intermediate portion. The first end is mounted to the high lift body, and the second end is mounted to the main wing by a roller bearing such that the track is movable along the longitudinal axis. The roller bearing includes a roller unit mounted to the main wing and having a circumferential roller surface engaging an engagement surface of the track and an internal elastic bearing allowing the roller surface, in a cross section parallel to the roller rotation axis, to adapt its orientation or form.

Abstract: An apparatus for fastening a component to an aircraft cabin attachment structure, the attachment structure having a fastening tube with a longitudinal axis. The apparatus has an internally bored sleeve rotatably positionable on the fastening tube and an external thread. A holding body connects to the component and has two spaced-apart limbs and a bearing surface enclosed by the limbs, and on which, an internal thread configured to the sleeve external thread, is arranged. A device fixes the holding body to the threaded sleeve and the fastening tube, the external and internal threads being non-self-locking. When the holding body internal thread presses against the threaded sleeve external thread, the threaded sleeve rotates until the external and internal threads align. The fixing device connects the threaded sleeve to the holding body in a rotationally fixed manner and fixes the holding body transversely with respect to the longitudinal axis.

Abstract: A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.

Abstract: A robotic manufacturing system includes a track extending along a length of a component of a partially manufactured item, wherein the component has a non-constant longitudinal shape, the track being supported independently of the partially manufactured item. The system includes a jointed member having an elongated arcuate shape, a mount longitudinally movable along the track and configured to receive the jointed member in an articulating manner, and an end effector movably mounted on the jointed member. The jointed member is movable along a portion of the component length in a radial position sympathetic to the non-constant component longitudinal shape. The jointed member is longitudinally movable relative to the mount along its elongated arcuate shape such that the jointed member will move in an arc spaced from and around an outer component surface. A portion of the end effector is movable along a length of the jointed member.

Abstract: A method for processing previously detected identifications of apparatuses of an aircraft, wherein each apparatus has at least one communicative component. A reference dataset is used to compare the actual identifications with specified identifications, as a result of which a report signal based on the comparison result indicates whether the detected identifications correspond to the identifications represented by the reference dataset. If there is a positive match, this allows the conclusion that the apparatuses are correctly installed in the aircraft.

Abstract: A method for producing a component from a fiber-reinforced plastic, wherein at least one ply of a semifinished fiber product having a peripheral contour is applied to the molding tool at a first temperature, wherein the contour lies within the peripheral edge. A compensating body, having a coefficient of thermal expansion which is greater than a coefficient of thermal expansion of the molding tool, is arranged along the peripheral edge, such that the compensating body extends from the edge in the direction of the peripheral contour. After sealing the arrangement, resin is introduced, and the arrangement is heated. As a result, the compensating body expands to a greater extent than the molding tool and encloses the semifinished fiber product in a flush manner, with the result that a shape of the component can correspond to an intended final shape and no longer has to be finish-machined.

Abstract: A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Abstract: A pipe connecting system for first and second pipe pieces extending along a common longitudinal axis includes a clamp. The pipe pieces each have first end and first clamping surfaces. The clamp has first and second contact surfaces lying against respective clamping surfaces to prevent the clamping surfaces from moving away from one another, while leaving a space between the first and second end surfaces. A retaining ring has a sealing connection attachment to the second pipe piece, and on which a sealing ring is mounted, the sealing ring lying against a circumferential first sealing surface of the first pipe piece. An interior of the first and second pipe pieces between the two pipe pieces is sealed against the surrounding environment by the sealing connection. The two pipe pieces can move towards one another without the first sealing ring moving out of contact with the first sealing surface.

Abstract: A system and method for welding two thermoplastic workpieces. The system has an ultrasonic tool, a support and a cooling unit. The ultrasonic tool is configured to generate mechanical vibrations. The system is configured to clamp together workpieces in the receiving region by the ultrasonic tool and the support if at least one fastening portion of the workpieces opposite one another is arranged in the receiving region. The ultrasonic tool is configured to introduce the mechanical vibrations into the fastening portion of the workpieces to weld the workpieces in a joining zone. The cooling unit is configured to cool, with cooling fluid, at least a part of the fastening portion of the workpieces and/or a cooling portion of the workpieces directly adjacent to the fastening portion.

Abstract: A structural element for a passenger cabin of an aircraft is built using biomimicry methods. The structural element includes a generative structure, and a functional component. The generative structure includes at least one accommodating space. The functional component is arranged within the at least one accommodating space. The generative structure includes a load topology optimized structure based on a bioinspired generative design that is configured to enable the structural integrity of the structural element while simultaneously providing integrated functionalities via the functional component. Further, an interior component for an aircraft is disclosed that includes at least one such structural element, and an aircraft including at least one structural element. For example, an aircraft galley may include a structural component that may therefore, for example, include integrated wiring, plumbing or other functionalities.