Abstract: A system for welding an elongate element along a longitudinal direction to a component including a support element comprising a support surface, a magnetic field generating arrangement generating a predefined magnetic field, a carriage comprising contacts supporting an elongate element against movement along the surface of the component in directions perpendicular to the longitudinal direction, a superconducting element being fixedly connected to the carriage, an element cooling device for cooling the superconducting element below its transition temperature, a mover operable to linearly move the carriage, and a welding device for welding the elongate element to the component. The predefined magnetic field defines a linear path along the support surface for the superconducting element when the superconducting element has a temperature below its transition temperature.

Abstract: A construction kit for a housing structure of a monument for a cabin of a vehicle, in particular of an aircraft includes a plurality of integrally formed sandwich panels which each have two cover panels, which surround a core, and are formed with panel connecting structures which are each formed as a plug region or as a mating plug region. The mating plug region is formed so as to be complementary to the plug region in such a way that a plug region of a sandwich panel can be plugged into the mating plug region of another sandwich panel to connect the sandwich panels.

Abstract: This relates to a System and a method for determining weight of freight units and baggage. Such a system comprises a Unit Load Device (ULD), an internal system of the Unit Load Device (ULD) and a digital memory unit, wherein the internal system is configured for retrieving individual identification and weight data of items within the Unit Load Device (ULD), for calculating a gross weight of the Unit Load Device (ULD) by summing the individual weight data of the items together with empty weight data of the Unit Load Device (ULD) and for storing a list of all identified items based on the identification data as well as the calculated gross weight of the Unit Load Device (ULD) in the digital memory unit.

Abstract: A monument for a cabin of a vehicle, in particular of an aircraft or spacecraft, having an outer housing side and a fastening rail for fastening connection elements in a longitudinal direction of the fastening rail in order to fix the monument in position inside the cabin, wherein the fastening rail has a receiving space extending in the longitudinal direction of the fastening rail, which space is designed to receive and fasten mounting feet of the connection elements to the fastening rail, and wherein the fastening rail is integrated in the outer housing side.

Abstract: Water supply vehicle comprising a water reservoir, a flow through descaling device having a water inlet, a water outlet, a detecting device for detecting a water characteristic in a water flow from the water inlet to the water outlet, a controllable water descaling device, and a controlling device being designed for controlling the water descaling device based on a water characteristic detected by the detection device, wherein the water reservoir is connected to the water inlet, wherein the water outlet is connectable to a water hose for supplying water to a water consumer.

Abstract: A flow body for an aircraft with a leading edge and a trailing edge includes a first spar, a second spar, and an external skin that spans from the leading edge to the trailing edge and on both sides rests on the spars. At least one of the first spar and the second spar includes a web and two spaced-apart flanges that enclose the web, on which flanges the skin that spans the respective spar is arranged. At least one of the first spar and the second spar includes at least one load introduction fin that forms an integral component with the web and extends outwards by way of one of the flanges and the skin that rests on the spars.

Abstract: A Wireless Access Point (WAP) for enabling remote access to data generated by systems of an aircraft including a wireless interface having a transmitter and a receiver; and a processor. The WAP is configured to: wirelessly receive sensor data generated by a plurality of sensors on an aircraft; receive aircraft data from an avionics system of the aircraft; wirelessly receive a data request signal from a remote computing device; and, responsive to the data request signal, wirelessly transmit to the remote computing device data based on received sensor data and/or received aircraft data.

Abstract: A galley module comprises a base galley section and a top galley section, wherein the base galley section comprises a top end adapted for carrying the top galley section. The base galley section comprises a first functional arrangement with a first access direction in a horizontal plane and the top galley section comprises at least one second functional arrangement having a second access direction in the horizontal plane. The first access direction and the second access direction enclose an angle of at least 90° in the horizontal plane.

Abstract: A load introduction element for a movable surface of an aircraft comprises a load introduction body that is connectable with the surface. A fitting connected with the load introduction body with a first section and a second section. The first section comprises a first bearing means, the second section comprises a second bearing means, and the first or second section comprises a third bearing means. The fitting is pivotally connected with the load introduction body by way of the first bearing means. An adjustment unit connects the second bearing means with the load introduction body in a variable position and is positioned on a side of the load introduction body that is opposite the fitting. In this manner adjustment of a reference position of a surface takes place without the need for an access flap. By loosening the adjustment unit the movable surface is pivotable without moving a flap drive.

Abstract: A door arrangement for an aircraft interior and an aircraft with such door arrangement, including a frame portion and a door blade hinged to the frame portion and pivotable between a closed position, where the door blade closes a door opening, and an open position, where the door blade allows access. The door arrangement includes a lever arm and an actuator mounted to the frame portion and operable to selectively move the door blade between the open and closed positions via the lever arm engaging the door blade and the actuator. The actuator is movable into a first actuator position and into a second actuator position. The actuator is movable into the second actuator position such that the door blade is able to move from the closed position towards the open position independent of the actuator while the actuator remains in the second actuator position.

Abstract: A setup device for manufacturing a fuselage barrel, made of a fiber composite material, for an aircraft is provided. The setup device for the purpose of reinforcement includes several stringers arranged so as to be spaced apart from each other. The stringers include a base structure to form a load-bearing rigid substructure that is connected to an outwardly curved supporting surface that can be adjusted by means of actuators for the positive setup of the fuselage barrel to be manufactured with the help of form channels for accommodating the stringers. The actuators, designed as pressure-means cylinders, move one or several form channels in radial direction. The form channels are interconnected longitudinally by means of a flexible intermediate element for forming a ring-shaped supporting surface that is closed in a vacuum-tight manner and that overall is able to adjust itself in radial direction.

Abstract: An aerodynamic sealing includes: an elastic first sealing wall extending between a first bottom edge and a first tip edge; an elastic second sealing wall extending between a second bottom edge and a second tip edge, and extending convergent with respect to the first sealing wall, so that the first and second sealing walls are joined together at their first and second tip edges to form a tip line; a bottom element connecting the first bottom edge to the second bottom edge, wherein the bottom element is joined to both the first sealing wall and the second sealing wall; and a plurality of stiffening elements connecting the first sealing wall to the second sealing wall between the tip line and the bottom element, wherein the stiffening elements are spaced apart from one another and joined to both the first sealing wall and the second sealing wall.

Abstract: A transport device for lithium batteries in an aircraft, in particular in a hold, includes a container and a lid, lithium batteries being arranged in the container and the lid closing the container during transport of the lithium batteries. A shutoff valve neutralizes electrolyte released by the lithium batteries within the container or conveys the electrolyte to the outside.

Abstract: A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, including: preparing an edge region of a first panel to form a first joining surface; preparing an edge region of a second panel to form a second joining surface; aligning the panels with one another such that the joining surfaces abut or interface one another forming a joint area; and joining the panels at the joining surfaces in the joint area. In an embodiment, the preparing steps include machining, and cutting, the edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously. In another embodiment, the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a primary plane or surface of the respective first and second panels.

Abstract: A device for use in drilling is adapted to be used in cooperation with a drilling unit that comprises a bush inside which a drill bit can advance and retract relative to the bush, the bush being provided with an opening from which the drill bit can protrude towards a workpiece or an arrangement of workpieces. The device includes a first portion and a second portion. The first portion is formed so as to fit into the opening of the bush. The second portion is formed so as to fit into a pre-drilled pilot hole in the workpiece or in at least one workpiece of the arrangement.

Abstract: An aircraft wing includes a main wing having an outer skin defining an interior space of the main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable in a predefined motion between a retracted position and at least one extended position. The assembly includes an elongate guide arranged within the interior space, a bearing at least partly arranged outside the interior space, an elongate slat track with a first end section connected to the slat and a second end section movably and rotatable connected to the guide, such that the second end section is movable along a predefined pathway defined by the guide while being connected to the main wing. An intermediate section of the slat track is movably and rotatably supported on the main wing, such that the guide and the bearing support the predefined motion.

Abstract: An assembly for producing a fiber composite workpiece having a base tool, including a first tool part and a second tool part, arranged relative to one another either in a closed position in which they enclose an internal space, or in an open position wherein a preform can be mounted in the internal space and maintained there in a predetermined shape. The base tool includes a connection to convey matrix material into the internal space, and has a device for holding the first and second tool parts together in a closed position. A tool insert is provided which is separate from the base tool, the tool insert being mounted in the internal space of the base tool, and the tool insert including a cavity for accommodating a preform and a shaping surface, facing the cavity, for maintaining the preform in a predetermined shape.

Abstract: An apparatus for manufacturing components from a fiber-reinforced composite material by a generative layer construction process including a control device and a tool head fastened to a carrier arm movable via the carrier arm in three spatial directions. The tool head comprises a feed device configured to feed to the tool head a semi-finished layer comprising reinforcing fibers impregnated with a curable plastic material. A shaping device, via movement of the tool head, applies a force to shape the semi-finished layer. A curing device introduces energy into the semi-finished layer, the energy curing the plastic material in the semi-finished layer. The control device controls the movement of the tool head as well as the operations of the feed device, the shaping device and the curing device wherein semi-finished layers are repeatedly fed, shaped, cured and stacked one on top of another to construct the component layer by layer.

Abstract: A support mandrel for producing curved composite components includes a prismatoid mandrel body formed from a flexible material, the mandrel body having two polygonal bases and an upper support surface extending between the two polygonal bases of the mandrel body, and a reinforcement bar enclosed within the mandrel body and extending between the two polygonal bases of the mandrel body substantially parallel and near to the upper support surface of the mandrel body.

Abstract: An induction heating system and a method for controlling a process temperature for induction heating of a workpiece. The induction heating system comprises an inductor configured to generate an alternating magnetic field in response to an alternating current supplied thereto, a magnetic load comprising a magnetic material, the magnetic material having a Curie temperature and being configured to generate heat in response to the alternating magnetic field being applied thereto, the magnetic load being connectable to the workpiece in a heat-conducting manner so as to transfer the generated heat to the workpiece, and a control unit configured to control the process temperature for manufacturing the workpiece by adjusting the alternating magnetic field when the temperature of the magnetic material is in a temperature control range around or below the Curie temperature of the magnetic material, the temperature control range being dependent on the magnetic material of the magnetic load.