Abstract: A cargo loading platform for an aircraft, with a plate-like supporting structure, which is configured to support or to receive cargo, and a lifting device. The lifting device is arranged asymmetrically on the plate-like supporting structure and can be moved from a stowage position to a lifting position. In the stowage position, the lifting device is arranged here above a lower side of the plate-like supporting structure and, in the lifting position, is at least partially arranged below the lower side of the plate-like supporting structure. This permits asymmetrical raising of the plate-like supporting structure by the lifting device, as a result of which steps during the transportation of the cargo loading platform can be easily and rapidly overcome. Furthermore, a cargo loading apparatus and a cargo container each with such a cargo loading platform, and also an aircraft with such a cargo loading apparatus are described.

Abstract: A device for lacquer transfer is disclosed having a frame, a transfer roller with a circumferential lateral wall, and a nozzle for dispensing lacquer. The nozzle is arranged contactless to or in direct contact with the outside contact surface of the lateral wall for dispensing lacquer into respective depressions in the lateral wall while the transfer roller is rotated about the axis of rotation. The transfer roller is configured to roll with the outside contact surface on a work surface of a work piece for transferring the lacquer from the depressions to the work surface of the work piece. The transfer roller includes a rim and a tire, wherein the rim is mounted to the frame rotatably about the axis of rotation by the first end and extends between a first end and a second end along the axis of rotation, wherein the tire is mounted on the rim and includes the lateral wall.

Abstract: A combined seat/stair arrangement for a multi-deck vehicle, in particular a multi-deck aircraft or spacecraft, include a foldable passenger seat; a stair which is designed to connect an upper deck to a lower deck via a stair hatch and at least one floor flap which movable between a use position of the stair with the stair hatch open and a use position of the foldable passenger seat with the stair hatch closed, wherein, in the use position of the foldable passenger seat, the at least one floor flap closes at least a partial region of the stair hatch, and wherein the floor flap is designed with a seat attachment, to which the foldable passenger seat is attached.

Abstract: A device for lacquer transfer includes a frame, a transfer roller with a circumferential lateral wall, a drive unit and a lacquer application unit. The lacquer application unit is mounted on the frame and applies lacquer to a work surface of a work piece while the device is moved in an application direction across the work surface. The drive unit drives the transfer roller in a rotation direction about an axis of rotation. An outside contact surface of the lateral wall comprises a plurality of depressions forming a predetermined structure. The transfer roller rolls with the outside contact surface on the work surface of the work piece for transferring the predetermined structure defined by the depressions in the outside contact surface to lacquer previously applied to the work surface by the lacquer application unit.

Abstract: A device and a method for supplying spare parts of an aircraft to a maintenance and/or repair center, such as a hangar. From data of previous transactions with the spare parts and from technical data relating to the spare parts, probabilities are calculated that certain spare parts are needed together, enabling them to be supplied together. According to a further aspect, different vending machines at the maintenance and/or repair center are proposed, with which the spare parts for a maintenance or repair task can be supplied together.

Abstract: A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.

Abstract: An on-board computing system for an aircraft. The computing system comprises a plurality of partitions each including at least one software component configured to perform a function related to the aircraft, wherein software components of different partitions of the plurality of partitions are configured to exchange data via a communication hub of the computing system, the communication hub being configured to store data items exported by exporting software components of the plurality of partitions and to provide the stored data items to reading software components of the plurality of partitions.

Abstract: A device for lacquer transfer includes a frame, transfer roller with circumferential lateral wall, nozzle for dispensing lacquer, and hardening unit, the hardening unit formed as a UV-light unit for hardening the lacquer in a contactless way by emitting UV-light, and is within an interior space defined by the transfer roller. The lateral wall of the transfer roller is transparent for UV-light, and the hardening unit is arranged such that UV-light is emitted towards the work surface upon which the lateral wall of the transfer roller rolls, to harden the lacquer after it being transferred to the work surface. Using the device, lacquer transfer can occur from the transfer roller to the work surface more reliably. The device includes a light shield between the hardening unit and outside contact surface with at least a portion of the outside contact surface provided with lacquer is shielded from UV-light emitted from the hardening unit.

Abstract: A structural assembly for an airfoil structure comprising at least one connection member configured to connect a leading-edge member, or a trailing-edge member, of an airfoil structure to a torsion-box member, such that the connection member prevents the leading-edge member, or trailing-edge member, from pivoting relative to the torsion-box member away from an operational position. At least one corresponding support is provided wherein the support is configured to be attachable to the connection member and further configured to be attachable to at least one system element.

Abstract: A rail for an aircraft floor includes an upper plate for supporting a set of floor panels covering the plate, and a lower stiffening structure. The rail is formed by a beam and by an anticorrosion protection. The beam is at least formed by a body made of a first material and defining the lower stiffening structure and an upper platform. The anticorrosion protection fully covers an upper face of the upper platform and forms therewith the upper plate of the rail, thus layered. The anticorrosion protection is at least formed by a protective sheet made of a second material that is more corrosion resistant than the first material and is selected from a metal and a fiber-reinforced plastic composite material. Such a rail exhibits good corrosion resistance at a moderate cost.

Abstract: A method for the production of stiffened components made of fiber-reinforced composite material using two rigid form tools which are suitable for covering the longer end sides of T-shaped preformed reinforcing fibers, using a folded hose core and inflation of the hose core so as to exert pressure on the end side of the preformed reinforcing fibers.

Abstract: A method for producing an aircraft structural component includes the steps of introducing a plurality of semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material into a compression mould, applying pressure to the stacked semi-finished product layers, the stacked semi-finished product layers being fixed, before pressure is applied, at particular points in their position in the compression mould and/or relative to one another in such a way that, while pressure is being applied to the semi-finished product layers stacked in the compression mould, a sliding movement of the semi-finished product layers relative to one another and/or relative to the compression mould, preventing wrinkling in the semi-finished product layers, takes place, and removing the aircraft structural component from the compression mould.

Abstract: A device for a lacquer transfer is disclosed having a transfer roller, the transfer roller includes a cylindrical support body, a first ring element, a second ring element, and a tire, wherein the tire comprises a middle section forming a circumferential outer contact surface with several depressions. The transfer roller is configured to roll with the outer contact surface on a work surface of a workpiece for transferring lacquer from the outer contact surface and from the depressions to the work surface of the workpiece. The tire includes two annular end sections, which are attached to the support body resulting in two axially separated and circumferentially extending connections. The tire, the connections, and the outer shell of the support body are fluid-tight and arranged such that a fluid-tight main cavity is formed between the tire and the support body.

Abstract: A rotary joint includes an inner joint element which has a spherically shaped inner convex joint face and an inner joint connection head protruding from the inner convex joint face; an outer joint element which has a spherically shaped inner concave joint face, a spherically shaped outer convex joint face and an outer joint connection head protruding from the outer convex joint face, wherein the inner joint element is held within the outer joint element such that the two joint elements can be rotated with respect to one another along the inner joint faces; and a joint bearing which has a spherically shaped outer concave joint face, wherein the outer joint element is held within the joint bearing such that the outer joint element can be rotated in the joint bearing along the outer joint faces.

Abstract: A leading edge structure (13) for a flow control system of an aircraft (1), including a double-walled leading edge panel having an inner wall element (45) and an outer wall element (47). Between the inner and outer wall elements (45, 47) are elongate stiffeners (49) spaced apart from one another. And, between adjacent stiffeners (49) are a hollow chamber (51). The outer wall element (47) includes micro pores (53). The inner wall element (45) includes passages (55) forming a fluid connection between the hollow chambers (51) and a vacuum system (15). An ice protection system in the stiffeners (49) includes hot air ducts (57) configured for connection to a hot air system (17), and the stiffeners (49) include hot air openings (59) forming a fluid connection between the hot air ducts (57) and the hollow chambers (51).

Abstract: A method for installing a preassembled internal fitting component of an aircraft, at least one luggage compartment being attached in an articulated manner to a fixing means and beside a ceiling lining and, optionally, a service unit being attached in an articulated manner to the luggage compartment and, likewise optionally, a covering element being attached in an articulated manner to the service unit. Following transport of the preassembled internal fitting component into a final mounting position, the individual elements of the internal fitting component can be mounted in the aircraft one after another by folding out and mounting. Also, a corresponding internal fitting component and to a system for mounting internal fitting components with a mobile mounting device.

Abstract: A rail covering for a sliding seat rail between two passenger seats in a cabin of a vehicle has a first and a second elongate covering element. The first and second covering elements are formed complementary with respect to each other, allowing the first covering element to telescopically engage with a lower side of the second covering element. The first covering element has, at least in regions on a lower side, a first guide which displaceably holds the first covering element on the sliding seat rail along the main direction of extent thereof. The second covering element has an open end arranged on the end side and, at an end arranged oppositely on the end side on a lower side, has a second guide which displaceably holds the second covering element on the sliding seat rail along the main direction of extent thereof.

Abstract: A control surface of an aircraft comprises a fixed skin panel, a first flexurally elastic skin panel and a second flexurally elastic skin panel, which is connected to the first flexurally elastic skin panel and is configured to at least partially overlap the fixed skin panel. Furthermore, the control surface comprises an actuator system, which is configured to move the second flexurally elastic skin panel parallel to the fixed skin panel, wherein the actuator system has a fixed structural element arranged in a root region of the control surface, and a structural element that is movable relative to the fixed structural element.

Abstract: A wing arrangement for an aircraft is disclosed including a wing having a fixed wing portion and a wing tip portion, wherein a the wing tip portion is pivotably connected to the fixed wing portion such that the wing tip portion is selectively pivotable about a pivot axis relative to the fixed wing portion between a first wing tip portion position and a wing tip portion second position, an actuator having an output element adapted to transfer an actuating torque and/or force to the wing tip portion for actuating the wing tip portion for movement about the pivot axis. The output element is movable between a first actuator position and a second actuator position, a first end stop for preventing movement of the wing tip portion beyond the first wing tip portion position, a detector adapted to detect a position of the output element, and a control unit adapted to control the actuating torque and/or force of the actuator based on the detected position of the output element.

Abstract: A wing for an aircraft having a fixed wing, a foldable wing tip portion rotatably attached to the fixed wing and an actuation unit for rotating the foldable wing tip portion relative to the fixed wing about a hinge axis is disclosed. The actuation unit includes a traction means for transmitting traction between the fixed wing and the foldable wing tip portion, a main wheel attached to the foldable wing tip portion and in contact with the traction means and a drive means for generating traction to be transmitted by the traction means. The actuation unit generates traction with the drive means in the traction means so that the foldable wing tip portion can be rotated relative to the fixed wing.