Patents Assigned to Airbus Operations
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Patent number: 8812180Abstract: The vertical profile management device includes a flight management system unit that selects a plurality of successive standard cruise sections, each comprising a level phase and a transition phase. The cruise sections are defined by a plurality of features, including waypoints corresponding to a section starting point and a section ending point, a transition type, a transition mode, a transition speed, a level altitude, and a level speed. The flight management system unit also joins together the successive cruise sections in order to form a vertical profile of a flight plan. The cruise sections are configured to be added, removed, or re-sequenced in the flight plan because each section ending point is configured to be the section starting point of a next cruise section in the series.Type: GrantFiled: March 16, 2012Date of Patent: August 19, 2014Assignee: Airbus Operations (SAS)Inventors: Maxime Wachenheim, Pierre Daste, Christophe Bouchet, Alexandre Lanoix, Romain Merat
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Patent number: 8807484Abstract: An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening.Type: GrantFiled: August 2, 2010Date of Patent: August 19, 2014Assignee: Airbus Operations LimitedInventors: Hugo Alexandre Duart Mendes Raposeiro, Bruno Stefes, Holger Bammann, Thomas Selchert, James Brown, Heiko Rothe, Alexander Solntsev
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Patent number: 8811654Abstract: A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.Type: GrantFiled: June 15, 2012Date of Patent: August 19, 2014Assignees: Airbus Operations GmbH, Premium Aerotec GmbHInventors: Tanja Frese, Klaus Edelmann
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Patent number: 8807161Abstract: The disclosed embodiments relate to a fuel line valve for an aircraft, that includes a shell capable of rotation inside the valve body and connected to a driving shaft driven by an electric actuator. The valve further includes a torque generation means and position detection means. The torque generation means are connected to the shell and generate a torque that varies based on the position of said shell in the valve body on the driving shaft. The position detection means provide electric signals characterizing the positions of said driving shaft. The disclosed embodiments also relate to a method for diagnosing the operation of such a valve in order to detect a failure during the operation thereof, and to a device for implementing said method.Type: GrantFiled: July 8, 2008Date of Patent: August 19, 2014Assignee: Airbus Operations SASInventor: Richard Wilby
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Patent number: 8806946Abstract: A system is provided for the detection of deposits in a fluid line that includes, but is not limited to a measuring body, and ultrasonic transducer and an ultrasonic receiver and at least one evaluation unit connected to the ultrasonic transducer and the ultrasonic receiver. The ultrasonic transducer transmits an ultrasonic signal and the ultrasonic receiver receives response signals generated by reflections in the fluid line. From known geometric changes in shape of the fluid line, resulting response signals are finally filtered out of the response signal sequence and from the remaining response signals relating to the deposits, the distances can be calculated between the ultrasonic transducer and the deposits.Type: GrantFiled: March 9, 2012Date of Patent: August 19, 2014Assignee: Airbus Operations GmbHInventors: Michael Flister, Wilhelm Lutzer
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Publication number: 20140224929Abstract: An aircraft area comprises a door, a door aisle and a main aisle. A storage cabinet for emergency equipment objects is disposed adjacent to the door aisle and/or the main aisle, and has an access point that is reachable from the door aisle and/or the main aisle.Type: ApplicationFiled: April 18, 2014Publication date: August 14, 2014Applicant: Airbus Operations GmbHInventor: Sebastian Weitzel
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Publication number: 20140224931Abstract: A cabin attendant seat comprising a carrier element which comprises a backrest section and a base section that carries said backrest section. A seat element is fastened to the carrier element. At least one first stowage compartment is integrated into said carrier element. A section of a rear wall of the carrier element is inclined, at least along a section of the stowage compartment integrated into said carrier element, in such a way that a cross-sectional area of said carrier element increases in the direction of the base section of said carrier element.Type: ApplicationFiled: April 18, 2014Publication date: August 14, 2014Applicant: Airbus Operations GmbHInventors: Sebastian Weitzel, Enrico Urban
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Patent number: 8800915Abstract: A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.Type: GrantFiled: March 30, 2012Date of Patent: August 12, 2014Assignee: Airbus Operations GmbHInventor: Martin Gerber
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Patent number: 8800917Abstract: An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.Type: GrantFiled: November 20, 2012Date of Patent: August 12, 2014Assignee: Airbus Operations SASInventors: Stephane Machado, Fabien Raison, Stephane Romani
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Patent number: 8800927Abstract: An aircraft door includes an outer skin configured as a panel structure; and a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity.Type: GrantFiled: April 29, 2010Date of Patent: August 12, 2014Assignee: Airbus Operations GmbHInventors: Marc Schimmler, Carsten Paul
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Patent number: 8805600Abstract: A flight control system includes at least one actuator for a mobile flight surface of an aircraft, and a flight control module in communication with the actuator. The module includes a first and a second computer. Each computer calculates a control command established according to at least one predetermined law for control of the flight surface. The first computer, known as validating computer, comprises logic means adapted for comparing its control command with that of the second computer, known as master computer, and for transmitting the result of the comparison to the actuator. The actuator comprises logic means adapted for deciding, on the basis of the result, to execute or not to execute the command of the master computer. An aircraft comprising such a system is also disclosed.Type: GrantFiled: January 20, 2010Date of Patent: August 12, 2014Assignees: Airbus Operations S.A.S., Le Centre National de la Recherche Scientifique (CNRS)Inventors: Manel Sghairi, Patrice Brot, Jean-Jacques Aubert, Agnan De Bonneval, Yves Crouzet
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Patent number: 8800277Abstract: A hydraulic system for aircraft wherein at least one circuit includes two hydraulic pumps, at least one of which is driven by an engine that may suffer uncontained failure that can damage hydraulic lines close to the pump, is equipped with pressure sensors for the hydraulic fluid in the lines close to the pump and a sensor for the hydraulic fluid level in a hydraulic tank of the circuit supplied by the pump. A control system for a cut-out valve installed on a suction line wherein the fluid arrives at the pump includes logic that determines the occurrence of an uncontained engine failure requiring the isolation of the pumps from line elements that may have been damaged from measurements of the fluid pressures in the lines, from measurement of the level of fluid in the tank and from information supplied late by a uncontained engine failure detection system to command the closure of the cut-out valve.Type: GrantFiled: October 22, 2008Date of Patent: August 12, 2014Assignee: Airbus Operations SASInventors: Roger Morvan, Nicolas Dubois, Cedric Lonjon
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Patent number: 8802224Abstract: Disclosed is a reinforcing material for the local reinforcement of a component formed with a composite material, in particular in areas of force introduction and/or connecting areas. The reinforcing material is formed by a metallic sheet-like formation, the metallic sheet-like formation having a surface with increased roughness to improve adhesion and a coating applied to the surface to provide a seal and improve the bond with the composite material. As a result of the presence of a coating on the metallic sheet-like formation, once it has been rolled up on supply rolls, said sheet-like formation can be drawn off from the supply rolls and at the same time processed in an automated manner by means of known computer-controlled laying devices with CRP prepreg materials in web form by laying layer by layer to produce components, in particular of large format, for aircraft.Type: GrantFiled: February 1, 2007Date of Patent: August 12, 2014Assignee: Airbus Operations GmbHInventor: Axel Herrmann
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Patent number: 8800921Abstract: A supporting component is provided for reinforcing the skin of an aircraft or spacecraft, for example a stringer or former, this component being configured as a closed profile (hollow profile), such that a system medium (M) can be conducted through the structural component. In this respect, the hollow profile itself serves as a load-bearing component.Type: GrantFiled: June 11, 2008Date of Patent: August 12, 2014Assignee: Airbus Operations GmbHInventors: Hinnik Gensch, Thorsten Roming
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Patent number: 8800924Abstract: An aerofoil structure (1) comprising at least two spars (2, 4) spaced apart in a fore and aft direction so as to define a fuel carrying volume between the spars, and at least one longitudinal corrugated reinforcing member (6, 7) disposed between the spars, each reinforcing member being corrugated in the longitudinal direction to form a series of forward ridges (9) on a forward side of the reinforcing member and a series of aft ridges (8) on an aft side of the reinforcing member, wherein each reinforcing member is directly attached by its forward ridges to one of the spars or to the aft ridges of an adjacent one of the reinforcing members, and wherein each reinforcing member is directly attached by its aft ridges to one of the spars or to the forward ridges of an adjacent one of the reinforcing members. Also, a method of manufacturing an aerofoil structure.Type: GrantFiled: January 14, 2010Date of Patent: August 12, 2014Assignee: Airbus Operations LimitedInventors: David Groves, Christopher Payne
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Patent number: 8800675Abstract: A fire extinguisher device for aircraft has a hanger structure and a reservoir of extinguishing agent, the aforementioned reservoir being hung beneath the aforementioned hanger structure by metal fittings held by fasteners to the aforementioned hanger structure. The aforementioned extinguisher wherein the reservoir has means of suspension and the hanger structure has carriers complementary to the means of suspension, the aforementioned means of suspension and the aforementioned carriers being such that when the fasteners are withdrawn, the reservoir is in a position called the “intermediate position,” in which the metal fittings are free and the reservoir is suspended by interaction of the means of suspension and the carriers. The disclosed embodiments also relate to a method for fastening such an extinguishing device.Type: GrantFiled: March 5, 2010Date of Patent: August 12, 2014Assignee: Airbus Operations SASInventors: Stephane Machado, Frederic Rossi, Julien Cayssials, Nicolas Voyer
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Patent number: 8800149Abstract: A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours in some areas and edges prone to damages occurring from handling and assembly of the panel. The process a) locates the damage in the element of the composite material panel; b) sands the area that includes the damage in an area larger than the damage, makes a cut in the panel, having the cut of a same form as a piece that will serve to repair panel; c) places the piece in the cut, so that it is perfectly flush with the panel to be repaired; and d) attaches the piece to the composite material panel.Type: GrantFiled: May 27, 2010Date of Patent: August 12, 2014Assignee: Airbus Operations S.L.Inventors: Alberto Balsa Gonzalez, Francisco de Paula Burgos Gallego
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Patent number: 8800916Abstract: A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane.Type: GrantFiled: May 1, 2012Date of Patent: August 12, 2014Assignee: Airbus Operations S.A.S.Inventor: Hervé Marche
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Patent number: 8800925Abstract: A holder assembly for a line installation in an opening of a support structure of an aircraft, includes at least one holder element to mount a line that is guided through the opening, with the line featuring a clamping section, arranged radially on the outside, to be attached to the opening as well as at least one central receiving section to fix the line, wherein the receiving section of a first holder element encompasses the line hook-like, and the receiving section of at least a second, oppositely positioned holder element also encompasses the line hook-like such that both hook-like receiving sections encompass the line.Type: GrantFiled: June 4, 2012Date of Patent: August 12, 2014Assignee: Airbus Operations GmbHInventor: Marc Schimmler
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Patent number: 8800928Abstract: The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.Type: GrantFiled: July 15, 2010Date of Patent: August 12, 2014Assignee: Airbus Operations GmbHInventors: Thorsten Roming, Hansjörg Horneber, Thorsten Schröer, Tobias Wirtz, Klaus Edelmann, Tanja Menken (Frese)
