Abstract: A device for building a three-dimensional structure in layers includes at least one supply unit, at least one laser unit and one table, wherein the table comprises a circular surface and is adapted for rotating the circular surface around a central axis. The supply unit is adapted for applying a powdery material in layers on the circular surface of the table. The laser unit at the same time can partly or completely melt powdery material already applied by the supply unit while the circular surface is rotating.

Abstract: A sandwich panel with at least one insert for forming a local reinforcement, which insert is smaller than a distance between the cover layers of the sandwich panel. A difference between the distance between the cover layers and a length of an extension of the insert including a previously viscous expansion compound with adhesive properties, which expansion compound has solidified during the pressing of the sandwich panel, is compensated for. A sandwich panel with at least one previously elastic insert whose original extension as a result of deformation during pressing of the sandwich panel is reduced. A method for producing such sandwich panels.

Abstract: A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.

Abstract: A system for producing a fiber-reinforced composite module, such as a panel module, having an integrated stiffening structure for an aircraft or spacecraft includes a form core assembly station for assembling a plurality of form cores covered with reinforcing fiber layers to constitute at least one stiffening element of the integrated stiffening structure, a form core placement station which receives assembled form cores from the assembly station for placing or depositing the assembled form cores in or on a molding tool, and a turning station for rotating or inverting the assembled form cores. The turning station is configured to convey or transport the assembled form cores from the assembly station to the placement station. The turning station defines a path which is configured to rotate or invert the assembled form cores as they are conveyed or moved to the placement station.

Abstract: An aircraft monument comprising a first compartment and a cabin attendant seat having a backrest and a seat element. The seat element is movable relative to the backrest between a folded position, wherein a seat surface of the seat element extends substantially parallel to a backrest surface of the backrest, and an unfolded position, wherein the seat surface of the seat element extends substantially perpendicular to the backrest surface of the backrest. The cabin attendant seat is movable relative to the aircraft monument between a stowed position, wherein the cabin attendant seat, with the seat element being in its folded position, is received in the first compartment of the aircraft monument, and an operating position, wherein the cabin attendant seat is disposed outside of the first compartment of the aircraft monument in a position which allows the seat element to be moved into its unfolded position.

Abstract: An aircraft door includes an outer shell with an exterior and an interior, a stiffening structure arranged on the interior of the outer shell, and at least one door seal arranged on the interior of the outer shell. The door seal is circumferential in an edge region. In the edge region between the outer shell and the door seal at least one circumferential stiffening component is arranged that is connected to the stiffening structure. Thus, in a particularly simple manner and without modifications to a stiffening structure, an aircraft door may be provided with very substantial stiffness in an edge region.

Abstract: A system for determining a cabin layout in a cabin of a vehicle, includes a system for contactless transfer of power with primary magnetic elements and secondary magnetic elements that each overlap with at least one primary magnetic element. Based on sequentially providing power to primary magnetic elements and measuring at least one electric value in the powered primary magnetic element overlapping states of secondary magnetic elements and primary magnetic elements can be determined. By determining overlapping states for all primary magnetic elements in the cabin the number and positions of all secondary magnetic elements and all vehicle components attached thereto can be collected. The system avoids powering two contiguous primary magnetic elements to prevent a wrong determination of an overlapping state.

Abstract: A tool to screw/unscrew a screwing element, having a module comprising a lever extending radially from and rotatable around a drive axis, a first transmission element rotatable around the drive axis by the lever, a transmission module comprising a second transmission element cooperating with the first element, a third transmission element rotatable around a screwing/unscrewing axis parallel to, and spaced from, the drive axis, a transmission system comprising an element transmitting the second element rotation to the third element, and an adapter with a fourth transmission element cooperating with the third element, and a cavity confirming to the screwing element. The tool includes a wedge with at least one rotatable adapter mounted thereon. The wedge comprises two support surfaces on planes parallel to the drive axis and disposed opposite one another to define a groove receiving an end of the transmission module on the third element side.

Abstract: A cargo compartment configured to be installed in an aircraft and to accommodate a plurality of cargo receiving devices is provided. The cargo compartment surrounds a compartment interior space, and includes a floor structure arrangement having a floor surface facing the compartment interior space and configured to support cargo receiving devices loaded into the cargo compartment. The cargo compartment includes two opposite side walls extending laterally of the floor structure arrangement away from the floor surface, and the side walls include an entrance opening for access to the compartment interior space. The floor structure arrangement also includes an air cushion device having a plurality of cushion nozzles distributed in the floor surface, and the cushion nozzles are configured to blow air up from the floor surface in a direction perpendicular to the floor surface.

Abstract: A system for damage tracking and monitoring during ground handling of aircraft includes a ground service communication network configured to transmit communication data between ground support equipment, GSE, and aircraft; a database configured to store configuration data and status data of GSE and aircraft; and a computer-based system configured to communicate with the ground service communication network and the database. The computer-based system is configured to update the configuration data and the status data of GSE and aircraft stored in the database on basis of communication data received from the ground service communication network. The computer-based system is further configured to estimate a damage source among the GSE for a damage inflicted on the aircraft by one of the GSE by correlating damage characteristics of the damage with the configuration data and the status data from the database.

Abstract: An aircraft includes a fuselage, each wing with a movable flap element arranged on the wing, having a sensor element providing a sensor signal corresponding to vibrations on the flap element, and being movable between a retracted and an extended positions, drive means having a movable driven output connected by an actuation assembly with each of the flap element and configured such that a movement of the output effects a movement of each of the flap element between the extended and retracted positions. A control unit is adapted to compare for each sensor element during operation of an excitation means the amplitude of the vibrations in the frequency interval detected by that sensor element with a predetermined threshold of that sensor element and to provide a failure signal when for at least one sensor signal the amplitude is below the threshold of that at least one sensor signal.

Abstract: A method for operating a control panel of an aircraft includes: sending display data from a control panel to a central controller of the aircraft, the display data including values to be displayed on a display screen of the control panel; loading, in the central controller, a display template from a central data storage, the display template including information for layouting the display data; generating a display page for the control panel in the central controller by merging the display data and the display template; sending the display page to the control panel; and displaying the display page on a display screen of the control panel.

Abstract: In a fiber composite component for an aircraft or spacecraft which has electrically conductive fibers at least in portions, the fibers are coupled with an electrical energy source for charging with current to heat up the fibers and/or for measuring the electrical resistance of the fibers.

Abstract: A fuel cell system includes a fuel cell having a housing that encases the fuel cell, a supply line for a fuel cell fuel, and an exhaust gas line for fuel-cell exhaust gas. In this arrangement the supply line extends in the exhaust gas line, and the exhaust gas line encases the supply line while forming a space. Any leakage in the supply line thus results in the fuel being flushed out by means of the exhaust gases flowing in the exhaust gas line so that higher system reliability and a reduction in costs can be achieved.

Abstract: A method for detecting a device that generates spurious signals in an electrical network, to which several devices and at least one fault detection device are connected, includes the steps of monitoring the electrical network for electrical spurious signals, sequentially deactivating each device for a predetermined time T when an electrical spurious signal has been detected, and checking the electrical network for the disappearance of the respective spurious signal, and signaling as soon as the respective spurious signal has disappeared upon deactivating a respective device. This makes it possible to especially reliably detect a device in an electrical network that couples an undesired spurious signal into the network.

Abstract: This relates to a multi-part attachment device for attaching a device to a stiffening element and to an outer skin of a vehicle. The multi-part attachment device comprises a base body having an angular profile for attaching the attachment device to the stiffening element and to the outer skin of the vehicle. Furthermore, the multi-part attachment device comprises an upper part with a lug, wherein the upper part is attached to the base body. This also relates to a method for attaching a device to a stiffening element and to an outer skin of a vehicle as well as to an aircraft with a multi-part attachment device.

Abstract: A casing for a lifting aid for an aircraft, comprising at least one strake which extends essentially in a protruding manner in the direction of flight in relation to an outer surface of the casing. An aircraft including a lifting aid and such a type of casing.

Abstract: A storage assembly, which is in particular suitable for use in a cooling system designed for an operation with a two-phase coolant medium, comprising a storage container with a receiving area for receiving a coolant medium and a conveying device for conveying coolant medium from the receiving area of the storage container. The conveying device is formed integral with the storage container of the storage assembly.

Abstract: An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network.

Abstract: A method for reinforcing a cellular material includes producing a through-hole in the cellular material that extends from a first surface of the cellular material to a second surface of the cellular material; reaching through the through-hole from the first surface of the cellular material to the second surface of the cellular material; taking hold of at least one fiber bundle at the second surface of the cellular material; and pulling the at least one fiber bundle into the through-hole in the cellular material. Producing the through-hole in the cellular material includes perforating the cellular material with a rotating and/or oscillating needle.