Patents Assigned to Airbus Operations GmbH
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Patent number: 9014840Abstract: A cargo loading system for a cargo compartment of a means of transport, for example a cargo aircraft or a passenger aircraft, is provided. The system includes at least one power drive unit for transporting cargo of the means of transport. The power drive unit and a control module are coupled to a BUS system. The control module generates control signals for the power drive unit and maintenance data of the power drive unit for the control and maintenance of the power drive unit. The BUS system transmits the control signals and maintenance data of the power drive unit between the control module and the power drive unit. In this manner an existing hardware platform of the means of transport can be used, and weight and cabling as well as the number of control boxes of the means of transport can be reduced.Type: GrantFiled: February 6, 2013Date of Patent: April 21, 2015Assignee: Airbus Operations GmbHInventors: Sven Scherenberger, Bernd Schnoerwangen
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Patent number: 9011219Abstract: A system for air-conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer, a first recirculation system designed to remove exhaust air from a first aircraft cabin region and connected to the central mixer, and a second recirculation system designed to remove exhaust air from a second aircraft cabin region and connected to a local mixer. A control device is designed to control the second recirculation system to reduce an air volume flow being removed from the second aircraft cabin region when shifting from a first operating state (e.g., normal operation) to a second operating state (e.g., defined operating situations such as when quick cooling is desired). The air volume being removed from the first aircraft cabin region may be increased accordingly in the second operating state.Type: GrantFiled: July 23, 2009Date of Patent: April 21, 2015Assignee: Airbus Operations GmbHInventors: Holger Brunnberg, Dariusz Krakowski
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Publication number: 20150104632Abstract: A mounting system includes a first and second mounting part having a first and second base part with a first and second plurality of first and second locking means respectively, for mounting two components to each other. Each of the locking means is attached to the respective base part and is provided with an attachment part extending from the base part, and a distal part provided as a head portion with at least one engaging section protruding sidewards over the attachment part. The locking means are laterally displaceable in relation to the base part to allow sidewards displacement of the engaging sections for engagement and disengagement of the locking means and thus the first and the second base. In the engaged state, latching means are provided blocking the sidewards displacement of the engaging sections to an extent that a disengagement of the locking means is prevented.Type: ApplicationFiled: October 13, 2014Publication date: April 16, 2015Applicant: AIRBUS OPERATIONS GMBHInventors: Sebastian Dyllong, Robert Alexander Goehlich
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Patent number: 9004405Abstract: A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.Type: GrantFiled: September 16, 2009Date of Patent: April 14, 2015Assignees: EADS Deutschland GmbH, AIRBUS Operations GmbHInventors: Marco Goettinger, Tamas Havar, Xavier Hue, Franz Stadler
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Patent number: 9005731Abstract: The present invention concerns a composite plate (1) comprising a first cover layer (3), a second cover layer (5), and a core layer (7) arranged between the first and the second cover layers (3, 5) and having a plurality of cells (9) which are at least partially open towards the first cover layer (3) and which are separated from each other by walls as well as a method of draining such a composite plate (1). In order to provide such a composite plate (1) in which improved resistance to ingress of liquid or formation of liquid accumulations is guaranteed in a simple and continual fashion it is proposed that a draining layer (13) is provided in the first cover layer (3), wherein the cells (9) are at least partially covered by the draining layer (13).Type: GrantFiled: May 18, 2007Date of Patent: April 14, 2015Assignee: Airbus Operations GmbHInventors: Stephan Hötzeldt, Oliver Schindler, Steffen Erfurth, Bernd Ohlendorf
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Patent number: 9003815Abstract: An aircraft air conditioning system has a fresh air line connected to a fresh air inlet for supplying fresh air to the air conditioning system and a sorption device disposed in the fresh air line which contains a sorbent for taking up moisture from the fresh air flowing through the fresh air line. The sorption device is adapted to expose the sorbent contained in the sorption device to ambient pressure surrounding an aircraft carrying the aircraft air conditioning system when the aircraft is flying for the purpose of regeneration of the sorbent. The sorption device is thermally connectable to a heat source that is adapted, when the aircraft is flying and while the sorbent contained in the sorption device is exposed to the ambient pressure, to supply thermal energy from the heat source to the sorbent contained in the sorption device for the purpose of assisting the regeneration.Type: GrantFiled: January 27, 2010Date of Patent: April 14, 2015Assignee: Airbus Operations GmbHInventor: Baker Al-Ali
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Patent number: 8998687Abstract: A supply system is provided that includes, but is not limited to a profile element. The profile element includes, but is not limited to a front wall, a rear wall, and webs between the front wall and the rear wall so that there are ducts within the profile element. The supply system also includes, but is not limited to at least one functional component integrated in at least one of the plurality of ducts.Type: GrantFiled: December 17, 2010Date of Patent: April 7, 2015Assignee: Airbus Operations GmbHInventor: Uwe Schneider
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Patent number: 8998143Abstract: A fairing device for creating an aerodynamic cover for an area of an aircraft structure, including a first fairing part with an outer side forming a first exterior flow contour, and having a fairing section for contacting a first section of the aircraft structure and a connecting section. The first fairing part includes a mounting device for receiving a connecting element. The fairing device includes a second fairing part including a fairing section having an outer side forming a second exterior flow contour and is designed for contacting a second section of the aircraft structure and a connecting section. The shape of the outer side of the second fairing part is adapted to the inner side of the connecting section of the first fairing part in an overlapping area, so the connecting section of the first fairing part forms a joint piece protruding over the second fairing part in the overlapping area.Type: GrantFiled: July 12, 2011Date of Patent: April 7, 2015Assignee: Airbus Operations GmbHInventor: Axel Sauermann
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Patent number: 8998313Abstract: 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.Type: GrantFiled: December 20, 2012Date of Patent: April 7, 2015Assignee: Airbus Operations GmbHInventors: Jan Reh, Andrew Muin, Martin Dehn, Peter Sander
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Patent number: 8998065Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.Type: GrantFiled: March 31, 2011Date of Patent: April 7, 2015Assignee: Airbus Operations GmbHInventors: Domenico Furfari, Marco Pacchione
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Publication number: 20150090840Abstract: A cargo door arrangement for an aircraft includes a fuselage portion, a cargo door and a locking mechanism. The fuselage portion includes a skin portion, at least one fuselage former and an opening. The cargo door includes at least one door former. The locking mechanism includes a first engagement element, a second engagement element and a connecting means. The first engagement element has a tapered portion and is rigidly connected to the door former. The second engagement element includes a tapered cavity having a shape matching the shape of the tapered portion and is rigidly connected the fuselage former. In the closed position the tapered portion is engageable with the cavity. The connecting means is adapted to rigidly connect in the closed position the door former to the first or second engagement element.Type: ApplicationFiled: September 24, 2014Publication date: April 2, 2015Applicant: Airbus Operations GmbHInventors: Andreas Jespersen, Felix Harden, Juergen Klare
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Patent number: 8991773Abstract: The present invention provides a device for mounting systems, for example an electrical or fluid-conveying line, on a structure, in particular of an aircraft or spacecraft, the device comprising a basic holder which is fastenable to the structure and a system holder for mounting the systems, the system holder being fastenable to a first interface of the basic holder, which system holder is fastenable to a first interface of the basic holder; the basic holder comprising a first part, which comprises the first interface, and a second part, one end of which is attachable to the first part so as to be pivotal about a pivot axis and the other end of which is fastenable to the structure.Type: GrantFiled: July 28, 2011Date of Patent: March 31, 2015Assignee: Airbus Operations GmbHInventors: Hans Peter Guthke, Barbara Lunitz
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Patent number: 8996735Abstract: A remote data concentrator (RDC) for an avionics network, the RDC comprising an input/output interface (I/O) for connection to one or more input/output devices, and a network interface for connection to a remote processor, wherein the RDC is operable to provide communication between the input/output device(s) and the remote processor, and wherein the RDC further comprises a set of instructions for autonomously driving an output device connected to the I/O. Also, an avionics network including the RDC; an aircraft including the RDC; and a method of operating the RDC.Type: GrantFiled: September 8, 2011Date of Patent: March 31, 2015Assignees: Airbus Operations Limited, Airbus Operations GmbHInventors: Timothy Todd, Thorsten Nitsche
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Patent number: 8991762Abstract: A wing-fuselage connection of an aircraft, in which a wing (2) that is arranged in the upper region of the fuselage (1) is connected to the fuselage (1) by means of a number of couplings (3, 4, 5, 6), wherein the couplings (3, 4, 5, 6) are provided for taking up forces in various directions and are designed for a maximum load carrying capacity, in particular for a nominal flight- and landing load (10) or a nominal crash load. According to the invention, the load carrying capacity of the individual wing couplings (3, 4, 5, 6) and their direction of force take-up are matched to each other such that in the case of a defect in one of the couplings (3, 4, 5, 6) the maximum load carrying capacity of the remaining couplings (3, 4, 5, 6) is adequate for safe normal flight operation.Type: GrantFiled: November 2, 2007Date of Patent: March 31, 2015Assignee: Airbus Operations GmbHInventors: Ursula Voss, Joel Rocker
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Patent number: 8991757Abstract: A cabin structural segment is provided for an aircraft that includes, but is not limited to a fuselage structure and a floor structure. The fuselage structure defines an interior and separating it from an environment. The fuselage structure includes, but is not limited to an opening for a door. It is possible to provide via the opening a connection between the interior and the environment. The cabin structural segment is designed to be self-supporting. The cabin structural segment is fastenable exclusively to the floor structure. The cabin structural segment is constructed in such a way that the one cabin structural segment frames the opening.Type: GrantFiled: May 24, 2012Date of Patent: March 31, 2015Assignee: Airbus Operations GmbHInventors: Peter Grosse-Plankermann, Martin Paetz, Markus Goslar
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Publication number: 20150082708Abstract: A cover plate for covering a door clearance between a skin of a means of transportation and a door as well as a door arrangement with such a cover plate is proposed. The cover plate includes a mounting region for permanently fastening the cover plate on the door; a covering region for covering the door clearance; and a fastening device that is designed for fixing the covering region on the skin when the door is closed.Type: ApplicationFiled: September 17, 2014Publication date: March 26, 2015Applicant: AIRBUS OPERATIONS GMBHInventors: Wolfgang Eilken, Matthias Hegenbart, Memis Tiryaki, Dirk Elbracht, Leonard Rahmel
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Publication number: 20150083862Abstract: A pressurized fuselage of an aircraft includes a fuselage structure and a pressure bulkhead mounted therein for forming a fuselage-internal pressure region. The pressure bulkhead is attached on the edge region, by way of mounting means, to the inside of the fuselage structure. The mounting means comprise at least one pivoting socket arrangement, arranged on the edge side of the pressure bulkhead, which edge side faces away from the pressure region, and interacts with the fuselage structure, as well as a supporting frame element, arranged on the opposite edge side and supporting itself on the fuselage structure.Type: ApplicationFiled: December 3, 2014Publication date: March 26, 2015Applicant: Airbus Operations GmbHInventors: Karim Grase, M. Ichwan Zuardy, Dieter Hachenberg, Henning Scheel, B. Claudio Vultaggio
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Publication number: 20150083860Abstract: A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements.Type: ApplicationFiled: September 19, 2014Publication date: March 26, 2015Applicant: Airbus Operations GmbHInventors: Holger Frauen, Robert Alexander Goehlich
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Patent number: 8986583Abstract: The invention relates to a pultrusion process in which a continuous reinforcement profile is formed by canting of at least one prepreg strip composed of a fiber-reinforced plastics material. The first shaping of the profile takes place in a preform device, which is downstream of a pressure-molding device for final shaping and prehardening. The movement of the profile takes place synchronously with respect to the operating cycle of the pressure-molding device by means of a traction device. By using a cutting device, it is possible to cut the profile to length and/or to subject edges to subsequent mechanical operations to ensure that correct dimensions are maintained. A continuous (pultrusion) gusset is inserted between the prepreg strips in a radius region of the profile. The gusset has an approximately triangular cross sectional geometry and it is formed by a plurality of continuous fibers braided with one another.Type: GrantFiled: July 2, 2007Date of Patent: March 24, 2015Assignee: AIRBUS Operations GmbHInventor: Michael Bechtold
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Patent number: 8989430Abstract: The present invention provides a flat speaker, in particular in the aerospace sector, with a panel for generating acoustic signals by vibration of the same, and a vibration exciter which is connected to a panel and excites this to vibrate. Here the panel has an edge stiffening. This provides the panel with the required stiffness, particularly against hand pressures, but at the same it guarantees high energy efficiency of the flat speaker.Type: GrantFiled: October 26, 2009Date of Patent: March 24, 2015Assignee: Airbus Operations GmbHInventors: Benjamin Grenzing, Henning Scheel, Frank Cordes