Abstract: A tolerance compensation subassembly in the form of a tolerance compensation element or a tolerance compensation region to improve the production, maintenance and repair of aircraft. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer so that the tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state. As a result, automation of the assembly of aircraft components on each other can be enabled or facilitated.

Abstract: For the exact lateral continuous positioning of material plies on a forming tool, a positioning device is provided to position a material ply on a forming tool during a production of a fiber composite component, comprising a positioning unit for positioning the positioning device in relation to a surface of the forming tool, a movement unit for moving the positioning device along a predetermined movement route along the forming tool, a route position detection unit for detecting the current route position of the positioning device on the movement route, and a material ply positioning unit for positioning the material ply in a direction transverse to the movement direction in dependence on the current route position detected by the route position detection unit.

Abstract: A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.

Abstract: An aircraft cabin assembly is depicted and described having a cabin wall, which surrounds a cabin interior space and has a wall surface facing the cabin interior space, and having a light source, which is provided in order to emit light onto the wall surface. The problem of providing an aircraft cabin assembly which, irrespective of the light outside of the aircraft cabin assembly, as effectively as possible gives a passenger in the cabin interior space the impression that the cabin interior space is larger than it actually is, is solved in that the wall surface has a holographic image of an object and in that the light source is designed to emit the kind of light onto the wall surface that allows the holographic image to be seen as a three-dimensional image of the object which is the subject of the holographic image.

Abstract: A method for manufacture of a complex component includes construction of the component from a metal material in an additive manufacturing method with at least one cavity segment that has a cavity open on at least one side and defined by an interior surface of the component, formation of an auxiliary electrode during construction of the component, formation of one or a plurality of supporting structures that connect the auxiliary electrode to the interior surface of the component during the construction of the component, electrical insulation of the auxiliary electrode from the interior surface by separating the supporting structures from the interior surface or from the auxiliary electrode, and performance of an electro-polishing of the interior surface in an electrolyte bath by connecting the component and the auxiliary electrode to different poles of an electric voltage source.

Abstract: A communication system for an aircraft comprises a communication interface with the outside of the aircraft and an avionics domain of which the security level is the highest of the communication system. It also comprises a communication domain to which is connected the communication interface and of which the security level is lower than the security level of the avionics domain. A barrier of a first type is arranged to filter the information coming from the communication interface so as to allow the information to pass into the communication domain only if the information corresponds to an authenticated communication. A barrier of a second type is arranged to filter information transmitted from the communication domain to the avionics domain, carrying out at least a syntactic filtering of the information.

Abstract: A device for determining a temperature in a passenger compartment of a vehicle comprising a sensor unit for detecting infra-red radiation and a temperature determining unit. The temperature determining unit may be configured so as, in dependence upon the measurement data provided by the sensor unit, to determine a surface temperature of a predetermined object located in the vehicle passenger compartment and, from the determined surface temperature of the object using a first functional relationship, to determine an air temperature in the vehicle passenger compartment. The temperature determining unit may be configured as an alternative or in addition thereto so as, in dependence upon the measurement data provided by the sensor unit, to determine a surface temperature for at least one passenger compartment occupant, and from the determined surface temperature using a second functional relationship to determine a measurement for the level of personal comfort.

Abstract: A system of fuel cells for an aircraft including a plurality of fuel cells, a hydrogen circuit, a cooling circuit and a first air circuit configured to supply oxygen to a first subset of fuel cells having at least two cells. The first air circuit includes an air flow restrictor at each fuel cell inlet of the first subset and configured to distribute the air between the fuel cells of the first subset, and an outlet valve connected to the outlet of the fuel cells of the first subset, the opening of the outlet valve being controlled by a computer as a function of an electrical power that is to be produced by the fuel cells of the first subset. The use of the same air circuit to supply oxygen to several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: The invention relates to a seat assembly for a cabin of a means of transportation, having an aisle which is arranged in the longitudinal direction of the cabin, two mutually spaced cabin walls which are oriented parallel to the aisle at least in some regions and laterally delimit the cabin, two outer passenger seat regions which are separated from one another by the aisle and each of which adjoins one of the two cabin walls, wherein the outer passenger seat regions have at least one row of seats with a respective inner first seat module which faces the aisle, a central second seat module adjoining the first module, and an outer third seat module adjoining the respective cabin wall.

Abstract: An actuating system for pivoting a wing tip section (13) about a fixed wing base section (11), and including a heating arrangement (33) positioned and adapted to be operable to heat at least one portion of an actuating arrangement (23) that pivots the wing tip section such that at least for ambient temperatures below a predetermined temperature the required work to be effected by the actuator (25) when moving the second coupling part (31) between the first position and the second position is lower than without heating the at least one portion.

Abstract: A process is proposed for producing a component, in which at least one first two-dimensional laid scrim is produced from a fibre composite material having a constant thickness, an outer face and an inner face. At least one second two-dimensional laid scrim is arranged with respect to the first two-dimensional laid scrim and then consolidated. The first two-dimensional laid scrim can be provided in a continuous, efficient production process, which increases speed and lowers costs.

Abstract: An inerting system and method for an aircraft includes an inert gas generation apparatus, an air supply line, a compressor and an inert gas line. The compressor supplies the inert gas generation apparatus with air from the air supply line at a pressure necessary for operation of the inert gas generation apparatus. The inert gas line carries the inert gas produced by the inert gas generation apparatus on to an inert gas consumer. The air supply line is connected to an exhaust air system of the aircraft. A method for supplying an inert gas in an aircraft includes tapping of air from an exhaust air system of the aircraft, compression of the tapped air, and production of inert gas in an inert gas generation apparatus from the compressed air. An aircraft is disclosed in which such an inerting system is arranged and/or used.

Abstract: An actuation unit (15) for actuating a foldable wing tip portion (9) of a wing (3) for an aircraft (1). The actuation unit (15) includes a track (25) configured to be mounted to a fixed wing (5), a carriage (27) configured to engage the track (25) for guided movement along the track (25), and configured to be coupled to a drive unit (31) for driving the carriage (27) along the track (25), and a link (29) configured to be coupled to the carriage (27) and configured to be coupled to a foldable wing tip portion (9).

Abstract: A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a first hinge (11) rotatable about a first hinge axis (13) between an extended position (15) and a folded position (17), and an actuation unit (19) arranged at the fixed wing (5) and coupled to the foldable wing tip portion (9) via a linkage (21) including a first link element (23) and a second link element (25), wherein the first link element (23) is mounted to a rotatable output (27) of the actuation unit (19) and is rotatably coupled to the second link element (25) via a second hinge (29), and wherein the second link element (25) is rotatably coupled to the foldable wing tip portion (9) via a third hinge (31).

Abstract: An oxygen supply system providing an adequate oxygen supply mode in an aircraft. A preventive oxygen supply system includes an oxygen source, a preventive oxygen dispensing unit connectable to the oxygen source, a cabin altitude detection device, and a preventive oxygen control device provide at least the following modes: a pre-wear mode providing no oxygen of the oxygen source to the preventive oxygen dispensing unit but normal cabin air; a pre-oxygenation mode providing a predetermined rate of oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for generating a pre-oxygenation condition of the user; and a decompression mode providing high concentrated oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for ensuring a minimum oxygenation of the user. The preventive oxygen control device automatically switches to the decompression mode in case a predetermined cabin altitude threshold is detected by the cabin altitude detection device.

Abstract: A device for fixing cabin side wall and cabin light paneling to a structural component of an aircraft and spacecraft includes: a structure holding component; and a cabin side wall holding component. The structure holding component has a surface for fixing the holding component to the structural component, and an adjustable surface for fixing the side wall holding component. The side wall holding component has an intermediate bracket and a side wall receiver for fixing cabin side wall paneling. The intermediate bracket is arranged between the adjustable fixing surface and the side wall receiver. The intermediate bracket has an intermediate guide element which guides the intermediate bracket, and the side wall receiver has a receiver guide element which guides the side wall receiver. The intermediate bracket has a fixing element for locking the intermediate bracket, and the side wall receiver has a fixing element for locking the side wall receiver.

Abstract: An airfoil arrangement which allows an increased reliability and increased aerodynamic performance of airfoils. A catching bracket is provided which is mounted in a track device opening to reduce the area of the track device opening and, when there is a failure of at least one support roller, the catching bracket engages the track device.

Abstract: A situation recognition device (10) including a surveillance processor (1) and an AI system (3). The surveillance processor receives visual and/or acoustic surveillance signals (E) from an aircraft passenger compartment (20) via an input interface (7). The AI system (3) includes an AI processor (4), a rule set generator (5) based on self-learning algorithms, and a reference rule set memory (6). The AI system is in bidirectional data communication with the surveillance processor (1). The AI processor (4) checks, upon a request (Q) from the surveillance processor (1), data patterns in the received visual and/or acoustic surveillance signals (E) for deviations from data patterns in a reference rule set (R) stored in the reference rule set memory (6). The surveillance processor (1) outputs indicator signals (A) via the output interface (8) if deviations determined by the AI processor (4) exceed one or more predefinable deviation threshold values.

Abstract: A device for a lacquer transfer includes a frame, transfer roller with a circumferential lateral wall, drive unit for rotating the transfer roller, and slit nozzle with a muzzle end for dispensing lacquer. The slit nozzle includes a first nozzle-part, second nozzle-part and deformation unit. The deformation unit is attached to the first nozzle-part, the lateral wall passing in a rotation direction subsequently the deformation unit and the muzzle end during transfer unit rotation. The lateral wall of the transfer roller is deformed by the deformation unit in the radial direction resulting in a deformation section of the lateral wall in the rotation direction behind the deformation unit, the muzzle end of the slit nozzle arranged for dispensing lacquer into depressions of the lateral wall. The transfer roller can roll with the outside contact surface on a work surface of a work piece for transferring lacquer from the depressions to the work surface of the work piece.

Abstract: A disruption device for fixing to an aerial vehicle. The disruption device is adapted to disrupt at least one radio path between at least one receiving unit of an unmanned flying body and at least one transmitting unit provided for controlling the flight path of the unmanned flying body. An aerial vehicle having the disruption device is further provided.