Abstract: A cabin attendant seat including a carrier element which comprises a backrest section and a base section that carries the backrest section and a seat element fastened to a front side of the carrier element. At least one first stowage compartment is integrated into the carrier element. An inclined section of a rear wall of the carrier element is inclined, at least along a section of the first stowage compartment integrated into the carrier element, in such a way that a cross-sectional area of the carrier element increases in the direction of the base section of the carrier element.

Abstract: An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft.

Abstract: A cooling unit in a transport unit includes power electronics; a heat exchanger for thermally coupling a cooling agent of a central cooling system of the transport unit with air of the cooling unit to cool one or more generating devices; and a heat pipe for heat dissipation of the power electronics. At a first portion of the heat pipe, at least some of a working agent is in the liquid phase and, at a second portion of the heat pipe, at least some of the working agent is in the gas phase. In the first portion of the heat pipe, heat from the power electronics is absorbed by evaporating the working agent in the liquid phase. In the second portion of the heat pipe, heat is released to the cooling agent by condensing the working agent in the gas phase.

Abstract: An aircraft region having an aisle which leads into an aircraft door region and via which passengers can leave the aircraft or enter the aircraft. The aircraft region further has at least one monument, wherein one of the side walls of the monument is adjacent to the aisle in such a manner that the side wall forms one of the lateral boundaries of the aisle. A niche is formed in a portion of the side wall of the monument facing the aircraft door, which niche is so configured that it is able to accommodate a standing person wholly or at least for the most part.

Abstract: A method for determining a state of a component in a high lift system of an aircraft, the high lift system including a central power control unit for providing rotational power by a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces, includes acquiring in an extended position in flight a first position of a first position pick-off unit coupled with the component, mechanically coupled with a high lift surface, and coupled with a drive station; acquiring in flight a second position of a second position pick-off unit arranged in or at the central power control unit in the extended position; determining a deviation between a first measure based on the first position and a second measure based on the second position; determining, whether the deviation exceeds a predetermined threshold; and if so, generating a signal indicating an abnormal state of the component.

Abstract: A system for cooling an aircraft zone includes a mixing chamber which is connected to an air-conditioning assembly for making cool air available and/or to a recirculated-air conveying device for supplying recirculated air into the mixing chamber. The system further includes an aircraft-side air-distribution system which includes at least one line connecting the mixing chamber to the aircraft zone to be cooled and also at least one line that is connectable to an aircraft-external air-generating assembly in order to route air made available by the aircraft-external air-generating assembly into the aircraft-side air-distribution system.

Abstract: A cooling system particularly suitable for use on board an aircraft includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough. An evaporator in the cooling circuit has a refrigerant inlet and a refrigerant outlet. A condenser in the cooling circuit has a refrigerant inlet and a refrigerant outlet. A detection device is configured to output a signal indicative of the state of aggregation of the refrigerant in a connecting portion of the cooling circuit which connects the refrigerant outlet of the evaporator to the refrigerant inlet of the condenser. A control device is configured to control at least one of the temperature and the pressure of the refrigerant in the connecting portion of the cooling circuit in dependence on the signal output by the detection device such that the refrigerant in the connecting portion of the cooling circuit is maintained in its gaseous state of aggregation.

Abstract: A test device and a test method for testing a drilling/rivet countersinking process carried out by a drilling/feed unit, a base body with at least one receiving groove and at least one turret mechanism with receiving openings being provided, the at least one turret mechanism being rotatably provided with respect to the base body in such a way that a predetermined receiving opening can be adjusted to align with the at least one receiving groove.

Abstract: A computer-implemented method, a computer program product and a device for the condition monitoring of a component or system, such as for an aircraft or spacecraft. The method includes: providing an optimized decision tree, the nodes of which contain attributes of an input vector, the leaves of which each contain a classification function and the connections of which between the nodes are weighted; providing an input vector derived from a data signal; implementing a condition monitoring in which the condition of the component or system is determined using the weighted decision tree and on the basis of the input vector. In addition to an item of information concerning which of the classification functions of the decision tree best corresponds to the input vector, an additional item of information concerning the probability with which the other classes of the decision tree correspond to the examined input vector is calculated and output.

Abstract: A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented.

Abstract: A composite skin for the aeronautics and astronautics industries, and also a method for producing a composite skin of this type is provided. The method comprises the following method steps: removing excess material from a butt plate to form a butt strap at one end thereof, subsequently connecting the other end of the butt plate to a skin plate with a substance-to-substance bond, and then fastening a further skin plate to the butt strap to form the composite skin. The idea behind the invention involves replacing a rivet connection with a substance-to-substance bond. This provides the advantage that the weight of the composite skin and the production costs for the composite skin are reduced.

Abstract: A holding arrangement for a mobile device in a cabin of a vehicle has a cabin equipment component, a support device arranged on the cabin equipment component, a holding device for holding a mobile device and a covering pane. The support device is designed to receive the holding device and further has an access opening arranged on a side opposite the cabin equipment component. Furthermore, the support device is designed to slidably hold the covering pane for opening and closing the access opening arranged on the side opposite the cabin equipment component in such a manner that the covering pane is movable to a closed position and to an open position, wherein in its open position the covering pane extends beyond the support device. Hereby, an improved holding function and temporary theft prevention may be accomplished.

Abstract: The invention relates to a supplementary power supply including a solar generator for ohmic consumers in a vehicle, in particular an aircraft, wherein a control circuit is electrically connected to a multiplicity of solar cells via generator terminals of the solar generator and includes at least one output terminal, and wherein the control circuit is configured to interconnect the at least one output terminal with the multiplicity of solar cells in accordance with an actual intensity of insolation of the solar cells such that a nominal voltage and/or a nominal current intensity is available at the at least one output terminal.

Abstract: A system for the contactless transfer of energy and data includes a transfer path with a primary coil and with a secondary coil. The primary control unit is designed to lead data-modulated first alternating-voltage signals of a first frequency range into the primary coil. The secondary control unit is designed to receive the first alternating-voltage signals of the first frequency range from the secondary coil, and to demodulate the modulated-on data. The system further includes a feed-in line for feeding a second alternating-voltage signal of a second frequency range to a primary line leading to a primary coil and an activation line that is connected to a secondary line that is connected to the secondary coil. A first filter filters the second alternating-voltage signal from the secondary line and provides the signal to an activation connection.

Abstract: A water amount controlling device includes a control unit for controlling an amount of water to be supplied, and a washing agent receptacle including a detection unit , wherein the detecting unit is adapted for detecting and identifying e.g. a type, a consistency or an amount of washing agent dispensed from a washing agent reservoir to be received in the washing agent receptacle, and wherein the control unit is adapted for controlling an amount of water based on the detected and identified property of the quantity of washing agent.

Abstract: A system for cooling and/or heating aircraft devices to be cooled and/or heated includes a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated, a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated, a cooling and/or heating energy supply apparatus adapted to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled and/or heated, a control device adapted to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system.

Abstract: The present invention provides a composite for an aircraft or spacecraft, comprising: a skin portion; a stringer which is attached to the skin portion; and a former made from fibre composite material, which is attached to the skin portion and forms an opening therewith, through which the stringer extends, substantially transverse to the former.

Abstract: The invention relates to a structural component, to a system and to a method for monitoring the integrity of a structure or a structural component. The structural component according to the invention has at least one elongated air duct which can be connected to a vacuum source and to a device for detecting the volumetric flow of air and/or the air pressure in the air duct, wherein, when the structure is intact in the region of the air duct, the air pressure in the air duct essentially corresponds to the air pressure of the vacuum source and there is essentially no volumetric flow of air through the air duct but, when a structural defect occurs in the region of the air duct, air from the region surrounding the structure or structural component enters the air duct and increases the air pressure and volumetric flow of air in the air duct in an identifiable manner.

Abstract: A universal joint member for transmitting torque between two shafts of a drive mechanism includes a first pivot axis for pivoting connection to a first shaft of the drive mechanism, wherein the first pivot axis extends substantially perpendicular to a rotational axis of the first shaft; and a second pivot axis for pivoting connection to a second shaft of the drive mechanism, the second pivot axis extending substantially perpendicular to the first pivot axis and substantially perpendicular to a rotational axis of the second shaft. A cavity extends through the universal joint member for receiving a pivot pin along the second pivot axis, wherein the pivot pin is configured to connect the universal joint member to the second shaft. A universal joint assembly for a drive mechanism includes a first rotatable shaft, a second rotatable shaft, and a universal joint member for transmitting torque between the first and second shafts.

Abstract: A sensor device for an oxygen module mountable on board an aircraft includes an electrical conducting element, a defining device for defining at least one measurement section, assigned to the oxygen module, on the electrical conducting element, and an evaluating unit for determining an electrical resistance present along the at least one measurement section, the evaluating unit further being configured to ascertain, based on the determined electrical resistance, whether the oxygen module is present. An aircraft has at least one oxygen module mounted on board the aircraft and at least one sensor device of the above type.