Patents Assigned to Airbus Operations GmbH
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Patent number: 8708786Abstract: An aircraft air-conditioning system includes an air-conditioning unit that is connected by a main fresh-air line to a mixer in order to supply the mixer with fresh air at a desired low temperature. A fresh-air branch line that is connected upstream of the mixer to the main fresh-air line has a flow cross section that is smaller than a flow cross section of the main fresh-air line. In a region of connection of the main fresh-air line to the fresh-air branch line the main fresh-air line and the fresh-air branch line are so formed that a main fresh air flow flowing through the main fresh-air line is deflected, while a fresh air branch flow flowing through the fresh-air branch line experiences substantially no deflection.Type: GrantFiled: December 23, 2009Date of Patent: April 29, 2014Assignee: Airbus Operations GmbHInventors: Martin Schmid, Dariusz Krakowski, Michael Markwart, Joerg Baumann
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Patent number: 8709188Abstract: The invention provides a method for producing a component (37) for aerospace, with the following method steps: supplying a lay-up arrangement (1) to be laid by means of a tape-laying machine (25), with a glass-fiber lay-up (8), which is preimpregnated with a resin matrix (10), and/or supplying a structural arrangement (12) to be laid by means of a tape-laying machine (25), with a structure (16) which is made of metal and is preimpregnated with a resin matrix (18), laying the lay-up and/or structural arrangement (1; 12) on a laminating apparatus (23) by means of a tape-laying machine (25), and curing the lay-up and/or structural arrangement (1; 12) and therefore forming the component (37).Type: GrantFiled: July 10, 2007Date of Patent: April 29, 2014Assignee: Airbus Operations GmbHInventors: Olaf Rocker, Manuel Jung, Thorsten Bleck
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Patent number: 8712227Abstract: Fluid conduit segments are provided that include, but are not limited to integrated heating systems for protection against freezing. To this effect PTC-fabric heating elements are provided that are integrated in the fluid conduit segments and that in the negative temperature range include, but are not limited to a PTC-temperature-dependent resistance. The heating system thus provides a higher output in the negative temperature range and a lower output in the positive temperature range, i.e., the heating limits itself until temperature equalization has been reached.Type: GrantFiled: May 5, 2011Date of Patent: April 29, 2014Assignee: Airbus Operations GmbHInventors: Juergen Meisiek, Torsten Maulitz
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Publication number: 20140113207Abstract: Fuel cell systems aboard means of transport can be used for generating energy and for producing water. In order to reduce the overall weight of the system, the fuel cell is controlled or regulated in dependence on a current fill level or a limit level of the water tank, as well as a predicted future water consumption. In this way, it may be possible to minimize the water quantity to be stored in the water tank.Type: ApplicationFiled: May 28, 2013Publication date: April 24, 2014Applicant: AIRBUS OPERATIONS GMBHInventor: Thorsten Otto
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Patent number: 8702038Abstract: A pressure fuselage of an aircraft or a spacecraft includes at least two fuselage sections disposed longitudinally along the fuselage; at least one pressure calotte disposed in the fuselage so as to form a pressurized area; and an arcuate frame profile having a Y-shaped cross-section with a long profile leg connected to at least one of the at least two fuselage sections and a short profile leg extending at an acute angle from the long profile leg toward an inside of the at least two fuselage sections and attached to the at least one pressure calotte.Type: GrantFiled: July 28, 2010Date of Patent: April 22, 2014Assignee: Airbus Operations GmbHInventors: Richard Bauer, Pierre Zahlen
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Patent number: 8706320Abstract: A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.Type: GrantFiled: November 29, 2012Date of Patent: April 22, 2014Assignee: Airbus Operations GmbHInventor: Roland Kelm
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Patent number: 8701708Abstract: A redundant gas supply or oxygen supply for an aircraft comprising two main lines and a group supply line that is connected to one consumer or to a multitude of consumers. In each case a connecting line connects the respective one main line to the group supply line. Flow limiters and nonreturn valves can be provided in the connecting lines.Type: GrantFiled: April 9, 2008Date of Patent: April 22, 2014Assignee: Airbus Operations GmbHInventors: Patrick Bricard, Emin Costan, Walter Deutscher, Thomas Vogt, Markus Wirth
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Patent number: 8702042Abstract: A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.Type: GrantFiled: April 9, 2012Date of Patent: April 22, 2014Assignee: Airbus Operations GmbHInventors: Martin Gerber, Geza Schrauf
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Publication number: 20140104732Abstract: A supply system for supplying energy in an aircraft includes at least one electrical line including at least one core connectable to a pole of a current source, an electrically conductive shield, and a detection unit having at least two electrical inputs. The shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield. At least one port of the detection unit is connected to the at least one core. At least another port of the detection unit is connected to at least one of the shield and the at least one core. The detection unit is adapted for detecting a differential current over the at least one core or an absolute current between the shield and a ground potential for generating a warning signal if a predetermined threshold value for the detected current value is exceeded.Type: ApplicationFiled: October 11, 2013Publication date: April 17, 2014Applicant: AIRBUS OPERATIONS GMBHInventors: Jens Schult, Torsten Stengel, Nicolas Fouquet
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Patent number: 8695922Abstract: An aircraft fuselage structure with frames (11) running transversely with respect to the longitudinal direction of the fuselage, and main deck cross members (14) is disclosed. The aircraft fuselage structure contains premanufactured integral units (10) which each comprise at least the lower region of the fuselage frame (11) and the main deck cross member (14), the fuselage frame (11) and a region (14a) of the main deck cross member (14) that spans at least an essential part of the width of the main deck and merges on both sides into the fuselage frame (11) being premanufactured in the form of an integral component.Type: GrantFiled: June 6, 2007Date of Patent: April 15, 2014Assignee: Airbus Operations GmbHInventors: Thorsten Schroeer, Thorsten Roming
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Patent number: 8695923Abstract: A window replacement for filling a window frame in an aircraft is provided, in particular a passenger aircraft, the window replacement being fixable by a retainer in the window frame in place of the window assembly when the window assembly is removed. The window replacement includes a panel-shaped element with at least a single curvature, the panel-shaped element being made of a synthetic material. The window replacement is formed by a monolithic panel-shaped element. The panel-shaped element of the window replacement may also be formed by a sandwich panel. This allows a weight reduction in comparison with a window replacement of a metallic material.Type: GrantFiled: September 13, 2007Date of Patent: April 15, 2014Assignee: Airbus Operations GmbHInventors: Ulrich Eberth, Mario Koeber
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Patent number: 8700253Abstract: A system is provided for collecting defect data of components in a passenger cabin of a vehicle that includes, but is not limited to a component identification device for identifying an affected component, and a malfunction selection device, connected to the component identification device, for selecting a malfunction of the identified component from a predefined quantity of component-specific malfunctions. The system includes, but is not limited to a locating device for acquiring a position of the affected component in the passenger cabin, with the aforesaid being connected to the component identification device. In this manner, by means of devices that are very simple to use, imprecise positioning information, component information and malfunction information can be avoided.Type: GrantFiled: August 25, 2011Date of Patent: April 15, 2014Assignee: Airbus Operations GmbHInventor: Daniel Fischer
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Publication number: 20140097662Abstract: A rail cover for a seat rail includes a cover element for completely covering a longitudinal portion of the seat rail. The cover element extends at least in part in a plane of extension that is formed by a longitudinal direction and a transverse direction of the rail cover and includes a first, rigid, longitudinal portion and a second longitudinal portion that follows on from the first longitudinal portion. The first longitudinal portion and the second longitudinal portion are mechanically coupled together by means of a flexible portion, wherein the second longitudinal portion is designed to carry out a pivoting movement in a direction across the plane of extension.Type: ApplicationFiled: October 7, 2013Publication date: April 10, 2014Applicant: Airbus Operations GmbHInventors: Thorsten Köhn, Carsten Wolgast
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Patent number: 8690102Abstract: A mounting assembly for the mounting of components in a body of a vehicle comprises at least one base element, at least one holding rail and connecting elements. The base element is designed to be arranged on the body of the vehicle. The holding rail is designed for mounting the components, and the base element and the holding rail are connected by the connecting elements so as to be spaced apart from each other.Type: GrantFiled: April 27, 2012Date of Patent: April 8, 2014Assignee: Airbus Operations GmbHInventors: Sebastian Umlauft, Henryk Wenzel
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Patent number: 8690453Abstract: The present invention relates to a plug/socket arrangement, in particular an electrical and/or optical plug/socket arrangement of an aircraft or spacecraft, which comprises a housing and at least one insert which can be received in the housing. It further comprises a releasable connection means which is adjustable between a locked position, in which the insert and the housing are locked to one another, and an unlocked position, in which the insert and the housing are not locked to one another; and an adjustment member which is adjustable between an inoperative position, in which the adjustment member is not operatively connected to the connection means, and a release position, in which the adjustment member is operatively connected to the connection means for releasing the locked position into the unlocked position of the connection means.Type: GrantFiled: January 18, 2011Date of Patent: April 8, 2014Assignee: Airbus Operations GmbHInventor: Guenter Schmitz
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Patent number: 8690107Abstract: A high-lift system with a main wing and adjustable flaps as well as guiding devices for holding the adjustable flaps and adjustment devices for adjusting the adjustable flaps, wherein the respective guiding device and/or adjustment device at least in part include/includes a fairing, including a flow influencing device for influencing the flow around the high-lift system, with at least one inlet line with at least one inlet that is situated on or below the bottom of the high-lift system, wherein, furthermore, at least one outlet line for air is provided that includes a fluid-communicating connection to the inlet line and includes at least one outlet situated at the top in the region of at least one adjustable flap of the high-lift system.Type: GrantFiled: June 22, 2012Date of Patent: April 8, 2014Assignee: Airbus Operations GmbHInventor: Burkhard Gölling
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Patent number: 8690487Abstract: An arrangement for adapting the transportation behavior of material to be conveyed includes a first container, which is coupleable to a first pressure level; a second container, which is coupleable to a second pressure level; a connecting line for transporting material to be conveyed from the first container to the second container; and a pressure reduction device by which a pressure difference between the first container and the second container is controllably variable.Type: GrantFiled: September 23, 2011Date of Patent: April 8, 2014Assignee: Airbus Operations GmbHInventors: Hannes Müller, Frank Schneider, Carsten Ohlfest, Frank Rahn
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Publication number: 20140090802Abstract: An aircraft thermal control system includes a thermal control unit including an internal circuit, an evaporator and a condenser, the evaporator and the condenser being disposed in the internal circuit. The aircraft thermal control system further includes a cooling circuit which is thermally coupled to the evaporator of the thermal control unit, and a heating circuit which is thermally coupled to the condenser of the thermal control unit.Type: ApplicationFiled: March 29, 2013Publication date: April 3, 2014Applicant: Airbus Operations GMBHInventor: Airbus Operations GMBH
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Patent number: 8686638Abstract: A lighting device having a plurality of light sources includes several superimposed layers. The superimposed layers include a first and a second electrically conductive layer, which are designed so as to create an alternating electrical field between the layers. The superimposed layers also have an electrically insulating layer between the electrically conductive layers and a luminescent layer between the electrically conductive layers. Electroluminescent material is arranged within the luminescent layer in several adjacent and spatially separated regions, each region forming a light source. As a result, a simulated starry sky may be provided when the lighting device is used with an aircraft interior trim panel.Type: GrantFiled: June 21, 2010Date of Patent: April 1, 2014Assignee: Airbus Operations GmbHInventors: Alexandra Marwede, Ronny Dehmel
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Patent number: 8685581Abstract: A fuel cell system (10) comprises a fuel cell (14) and an evaporative cooling system (16), which is in thermal contact with the fuel cell (14), in order that heat generated by the fuel cell (14) during operation of the fuel cell (14) is absorbed through evaporation of a cooling medium and is removed from the fuel cell (14). The fuel cell system (10) further comprises a device (22) for sensing the pressure in the evaporative cooling system (16). A control unit (24) is adapted to control the operating temperature of the fuel cell (14) in dependence on signals that are supplied to the control unit (24) from the device (22) for sensing the pressure in the evaporative cooling system (16), in such a way that the cooling medium of the evaporative cooling system (16) is transferred from the liquid to the gaseous state of matter by the heat generated by the fuel cell (14) during operation of the fuel cell (14).Type: GrantFiled: May 14, 2013Date of Patent: April 1, 2014Assignee: Airbus Operations GmbHInventor: Tobias Scheibert
