Abstract: The present invention provides a server system, in particular for an aircraft or spacecraft, comprising an integration device which has at least two server modules which have in each case at least one program-controlled arithmetic-logic means, at least one memory which is coupled with the program-controlled arithmetic-logic means, and at least one communication interface which is coupled with the program-controlled arithmetic-logic means, comprising at least one data line which interconnects the two server modules for data communication by the communication interfaces thereof, and comprising a server interface which is configured to connect the integration device to a data network for data communication by the communication interfaces of the server modules, the integration device being configured to exchange data with the data network. The present invention also provides an aircraft or spacecraft and a method.

Abstract: A test system for plug-in connectors, especially for plug-in connectors in an airplane. A transmitting device which is designed for sending out a test signal to the plug-in connectors to be tested, and comprising at least one receiving device for each plug-in connector to be tested which is electrically coupled with the respective plug-in connector and which is designed for receiving the transmitted test signal and outputting an acknowledgement signal in response to receiving the transmitted test signal. Furthermore, the present invention creates an aircraft or a spacecraft and a method.

Abstract: An aircraft (F) with wings (1; 1a, 1b) and a system for minimizing the influence of unsteady flow states, wherein the wing consists of a respective main wing (M) and at least one control flap (S) adjustably arranged relative thereto, a adjusting drive (21) for activating the at least one control flap (S), as well as a sensor arrangement for acquiring the setting position of the control flap (S), wherein the system for minimizing the influence of unsteady flow states exhibits: At least one arrangement (15) of flow-influencing devices (16) for influencing the fluid flow over the surface segment (10), which are functionally connected with the flight control device, and incorporated in at least one surface segment (10; 11a, 12a; 11b, 12b) of the main wing (M) of each wing (M; 1a, 1b) extending in a respective wingspan direction and/or at least one control flap (S), A detection device for detecting unsteady flow states acting on the aircraft, An actuating function that is functionally connected with the flow-in

Abstract: An adjustment system of an aeroplane, having: at least one adjustable flap on each of the wing of an aeroplane, adjustable with an adjustment device, a drive device for purposes of driving the adjustment devices, and a load sensor for purposes of recording the load occurring in the load path between the actuator and the adjustable flap of the respective adjustment device. The load sensor is embodied as a sensor for purposes of measuring the longitudinal force occurring in a drive rod along its longitudinal direction.

Abstract: A molding tool for manufacturing a fiber-reinforced plastic aerodynamic aircraft component, which aircraft component, in order to form several bays arranged on the inside and delimited by an outer skin and spars arranged spaced apart from each other, in each case includes a multi-part mold core that matches the shape of the respective bay, wherein to conform to local skin reinforcements and/or spar reinforcements that extend into at least one of the bays, the multi-part mold core includes four or five core parts, of which two core parts comprising a triangular cross section are arranged along opposing edges of the bay, which edges interact with two or three core parts that fill the space between the two triangular core parts, which space extends diagonally relative to the bay.

Abstract: A passenger seat has a backrest and a seat which has first and second sections each having a first surface for a seat area and a second opposite surface. The second section pivots relative to the first section between a first position, in which the first surfaces of the first and second sections form a usable total seat area, and a second operational position, in which the second section is folded relative to the first section in the direction towards the backrest. Attached to the second seat section is a holder movable relative to the second surface of the second seat section between a first position, in which the holder extends substantially parallel to the second surface of the second seat section, and a second position, in which the holder extends at from 60° to 120° relative to the second surface of the second seat section.

Abstract: A priority valve assembly includes a fluid supply line, a first fluid discharge line, and a second fluid discharge line, both of which are to be supplied with fluid via the fluid supply line. A priority valve throttles a fluid flow from the fluid supply line into the second fluid discharge line to prioritise the supply of fluid to the first fluid discharge line over the supply of fluid to the second fluid discharge line if a control parameter which is characteristic for an inlet fluid pressure (pE) in the fluid supply line falls below a first predetermined threshold value (p2). The priority valve reduces the throttling of the fluid flow from the fluid supply line into the second fluid discharge line if the control parameter falls below a second predetermined threshold value (p4) which is smaller than the first predetermined threshold value (p2).

Abstract: An air-sucking vehicle fuselage component includes an outer delimitation part, and inner delimitation part, and connecting elements. The inner delimitation part is connected via the connecting elements to the outer delimitation part. The outer delimitation part includes a continuously curved shape. The inner delimitation part includes two or more flat delimitation part components, which are each connected to one another at one edge to form a connection edge, and the connection edge is configured to be attached to the outer delimitation part. A type of framework structure is thus provided, which causes increased stability and can split impacting objects in particular if two inner delimitation part components are used on the vehicle fuselage component.

Abstract: A retaining device for a component of an aircraft or spacecraft. The retaining device comprises a fuselage cell portion and a component portion, which portions are interconnected via at least one fastener. A gap is formed between the fastener and the component portion, of such a type that the fuselage cell portion and the component portion are movable relative to one another.

Abstract: A system for inductive contactless power transfer between a first vehicle part and at least one collector that can be variably positioned relative to the first vehicle part in a passenger cabin of a vehicle includes primary windings (P1-PN) that with secondary windings (S1, S2) on collectors or second vehicle parts can form a transducer. Depending on operating-mode switching of the vehicle, the operation of collectors is prevented, which collectors for the purpose of providing electrical power for operating external cleaning or maintenance devices are brought into the vehicle. Because of the expansion of the function of an existing contactless power and data transfer system, the system is particularly cost-effective and flexible, and in addition is of a very lightweight design.

Abstract: A vehicle window with a primary window pane arrangement, a secondary window pane that is spaced apart from the primary window pane arrangement and a window funnel that extends between the secondary window pane and the primary window pane arrangement is provided. The vehicle window includes an intermediate space that is formed by the window funnel, the secondary window pane and the primary window pane arrangement, and the intermediate space is sealed and equipped with an air inlet for introducing dehumidified air into the intermediate space. Due to the seal, humid air leading to condensation and frost in the intermediate space is prevented from flowing into the intermediate space during a pressure compensation flow. The passenger comfort is enhanced due to the improved view through the window.

Abstract: A covering device includes a sealing element and a rib structure which is disposed on a surface of the sealing element. The rib structure includes a plurality of ribs which extend parallel to the surface of the sealing element, wherein the bendability of the ribs parallel to the surface of the sealing element is high, and perpendicular to the surface of the sealing element is low.

Abstract: A sealing system for an aircraft device to be sealed off from the environment includes a door, which, when connected to the housing, is movable between an open position, in which the door clears a door aperture in the housing, and a closed position, in which the door closes the door aperture. The sealing system includes a sealing element, on which a sealing surface is formed, wherein the sealing surface is adapted to interact sealingly with a contact surface when the door is situated in its closed position. A positioning device is provided, which is adapted to move the door substantially at right angles to the sealing surface or to the contact surface between a first position, in which the sealing surface is not movable into sealing contact with the contact surface, and a second position, in which the sealing surface is movable into sealing contact with the contact surface.

Abstract: A passenger monitoring and directing system for use in an aircraft cabin is provided. This system includes at least one information unit to be arranged in the aircraft cabin and at least one passenger monitoring device. The information unit includes at least one monitoring portion and the passenger monitoring device is assigned to the information unit and arranged relative to its monitoring portion in order to monitor the passengers through the monitoring portion of the information unit.

Abstract: Systems and methods are provided for the loading and unloading of cargo in transport means. In one example, a cargo loading system having a fully automated conveyor system and a fully automated bolt system for locking the cargo unit is provided. Manual interventions of the loading personnel in the cargo space may not be necessary.

Abstract: A system for repairing a structural component, in particular an aircraft structural component, includes a repair patch which is connected to the structural component in such a manner that it covers an opening in the structural component resulting from removing a damaged region of the structural component. A sensor is fastened to the repair patch in a region of the repair patch covering the opening in the structural component and is designed to detect strains and/or stresses occurring in the repair patch. An evaluating device is adapted to evaluate the strain values and/or stress values detected by the sensor and, in dependence on the result of this evaluation, output a signal which is characteristic of the quality state of the connection between the structural component and the repair patch.

Abstract: A computing unit allocates boarding paths, available for boarding a transport unit, in particular an aircraft, to passengers of the transport unit. An associated method allocates boarding paths, available for boarding the transport unit to passengers of the transport unit. A computer program carries out the method, and a directing system directs passengers of the transport unit along boarding paths available for boarding the transport unit. The computing unit is configured to form two or more changeable seat groups from a plurality of seats provided in the transport unit and to allocate the boarding paths, available for boarding the transport unit, to the two or more seat groups formed.

Abstract: An air-conditioning system for an aircraft includes a compressed air branch for conveying externally supplied and pressurized air, preferably bleed air. Furthermore, a cooling circuit for conveying preferably liquid refrigerant is provided and extends through a ram air duct. The system also includes a first heat exchanger for the heat transfer between the compressed air branch and the cooling circuit, a compressed air turbine arranged in the compressed air branch and a cooling circuit compressor arranged in the cooling circuit and mechanically coupled to the compressed air turbine. The system can have a modular design and be positioned at optimal locations in the aircraft due to the separation of the compressed air branch and the cooling circuit. In this way, the length of hot compressed air ducts can be shortened.

Abstract: An accumulator arrangement suitable for use in a cooling system designed for operation with a two-phase refrigerating medium, includes an accumulator vessel with a receptacle for receiving a refrigerating medium. A liquefier of the accumulator arrangement is adapted to liquefy refrigerating medium to be received into the receptacle of the accumulator vessel before fed in the receptacle of the accumulator vessel and includes a refrigerating medium outlet for discharging refrigerating medium which liquefied in the liquefier from the liquefier.

Abstract: A riblet structure for a flow surface is provided. The riblet structure has a multitude of riblets that comprise a matrix material which includes reinforcement elements. The reinforcement elements can be designed as reinforcement fibers that extend in the longitudinal direction or as particles. In this manner the abrasion resistance can be improved and erosion can be retarded.