Abstract: The present invention describes composite rods keeping two elements apart a determined distance carrying the loads between them, such as railways, industrial premises, etc. Besides, the manufacturing method thereof and the tool involved in this process are also described.

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: The invention relates to a wall made from a composite material comprising at least two layers of fibers (18, 18?) embedded in a resin matrix, a crack being able to spread in said wall in a direction of propagation, characterized in that it comprises at least one longilineal metal reinforcement (20), oriented in a direction secant to the direction of propagation, inserted between two layers of fibers (18, 18?) of the wall.

Abstract: A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them.

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 system for controlling energy of a vehicle, for example an aircraft, characterized in that it comprises: a control interface (10), said control interface comprising a movable element (12) configured to move along a path (13), said path defining at least two path portions (14, 17) respectively associated with at least two combinations of actuators acting on the energy of said vehicle, at least one of said at least two combinations of actuators being associated according to a current phase of movement of the aircraft, and a control unit configured to generate an energy instruction according to a command associated with a current position of said movable element on one of said at least two path portions, and according to said current phase of movement of the vehicle, said instruction being for the associated combination of actuators.

Abstract: A tool for manipulating a transducer assembly. The tool had a shaft to space the transducer assembly from a handle end. The tool rotatably mounts the transducer assembly so that the transducer assembly can transmissively coupled to and follow an arcuate scanning path. The tool includes a guide member for following an edge of a component to be tested.

Abstract: The invention relates in particular to a method and a system for monitoring a graphical interface in a computer system of an aircraft cockpit. The method comprises, in addition to the display of a graphical interface of a client application based on a tree structure of graphical interaction objects composing said graphical interface, the following steps: obtaining a plurality of graphical interaction objects having a tree-structure organization; creating and adding, to said obtained tree structure, at least one new graphical interaction object defining a critical graphical display zone; modifying the tree-structure dependency of at least one critical graphical interaction object, of the obtained tree structure to make it dependent from the new graphical interaction object defining the critical zone; and performing critical monitoring only of the critical graphical objects attached to the critical zone.

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 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: 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 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 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 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: 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: 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: An insulation device for an aircraft, comprising a blanket comprising a layer of insulation filling enclosed in a cover and having provision areas for the passage of aircraft components, these areas being devoid of insulation filling and being formed by a surface junction of two opposite faces of the cover inducing a recess in at least one face. The insulation device comprises an associated detachable complementary assembly to cover at least one of the provision areas, the assembly comprising a portion of insulation filling shaped to fit into the corresponding recess, and a retention arrangement for retaining this portion of filling. The retention arrangement is provided with a detachable arrangement for fixing the detachable complementary assembly on at least one face of the cover.

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: 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.