Patents by Inventor Airbus Operations (SAS)

Airbus Operations (SAS) has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20130200652
    Abstract: The invention relates to a method for producing a fiber composite workpiece. In the method according to the invention, cross-linking silicone is used with the aid of a volatile diluent for infiltrating individual mats of a mat composite. A further object of the present invention is a device for performing the method according to the invention.
    Type: Application
    Filed: January 9, 2013
    Publication date: August 8, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130200216
    Abstract: The invention relates to a device for producing an inert gas that comprises a fuel tank for a fuel, at least one fuel cell with a cathode, an anode, a reactor for reforming fuel from the fuel tank into a hydrogenous fuel gas and an inert gas outlet. The reactor comprises a fuel gas outlet that is connected to a fuel gas inlet arranged on the anode of the fuel cell. The inert gas outlet is arranged downstream of the reactor and forms a fluid sink for non-hydrogenous reaction products of the reactor.
    Type: Application
    Filed: January 29, 2013
    Publication date: August 8, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130204470
    Abstract: A method and computer program product for planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, including providing a stabilization flight path section and stabilization region and/or stabilization point defined by an altitude profile by at least one configuration change point in the stabilization flight path section with a change of the overall profile configuration of the airfoils and with a predetermined final approach flight status of the aircraft, and checking or changing position of the at least one configuration change measure in a change and/or the addition of an additional configuration change measure to the stabilization flight path section and by changing a speed profile along the stabilization flight path section so that the aircraft reaches the predetermined final approach flight status in the stabilization region or at the stabilization point.
    Type: Application
    Filed: January 23, 2013
    Publication date: August 8, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130199201
    Abstract: An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced.
    Type: Application
    Filed: March 7, 2013
    Publication date: August 8, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations Gmbh
  • Publication number: 20130192345
    Abstract: A device for carrying out a test on a fluid circuit of an aircraft including a test unit which includes, at the inlet, at least one means of connection to a pressurized gas supply connected to means for regulating the pressure of the gas provided by the supply as a function of the test to be carried out and, at the outlet, at least two connection means connected to the means for regulating the pressure of the gas, wherein at least two connection means have different dimensions tailored to a range of pressures or a given pressure.
    Type: Application
    Filed: March 13, 2013
    Publication date: August 1, 2013
    Applicant: AIRBUS OPERATIONS SAS
    Inventor: Airbus Operations SAS
  • Publication number: 20130187012
    Abstract: A device and method for securing a plurality of electrical conductors in a bundle. The device (10) comprises first and second portions (12a, 12b) connected so as to be moveable between a closed configuration in which the first and second portions define at least one enclosed space which extends through the device and an open configuration in which a conductor may be moved laterally into the at least one space from the periphery of the device. The device further includes a plurality of recesses (20) for receiving conductors disposed around its peripheral edge.
    Type: Application
    Filed: January 17, 2013
    Publication date: July 25, 2013
    Applicant: AIRBUS OPERATIONS LIMITED
    Inventor: Airbus Operations Limited
  • Publication number: 20130191087
    Abstract: The invention is aimed at a method simulating the aerodynamic flow around an aircraft, so as to detect the aerodynamic loads exerted on a predetermined surface of the aircraft. The method includes a phase of determining a value denoted QA of global dynamic pressure at the level of the predetermined surface of the aircraft. The method includes steps of carrying out simulations of aerodynamic flow around the predetermined surface of the aircraft for given environmental conditions, on the basis of a mesh produced around the shape of the aircraft, determining a local dynamic pressure qA around the predetermined surface of the aircraft, and then calculating the global dynamic pressure QA.
    Type: Application
    Filed: October 26, 2012
    Publication date: July 25, 2013
    Applicant: AIRBUS OPERATIONS SAS
    Inventor: Airbus Operations SAS
  • Publication number: 20130187009
    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
    Type: Application
    Filed: January 4, 2013
    Publication date: July 25, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130183082
    Abstract: A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of projections extending from a bond surface of the first component, each projection having a base, a tapered tip and a tapered overhang beneath the tip, wherein the overhang has an undercut surface which is inclined and faces towards the local bond surface; bringing the components together so as to embed the projections in the second component; and hardening the second component after the array of projections has been embedded into it. Also, a joint so formed.
    Type: Application
    Filed: March 5, 2013
    Publication date: July 18, 2013
    Applicant: AIRBUS OPERATIONS LIMITED
    Inventor: Airbus Operations Limited
  • Publication number: 20130181509
    Abstract: An interface device between an electrical network and energy consumer systems, including an input converter with a first winding connected on one side with a reverse blocking module and on the other with a first semiconductor chopper device, second and third windings having an end connected to output converters via first and second reverse blocking modules, and another end connected to the output converters, via a switching cell, a fourth winding having an end to be connected to the network, via a second semiconductor chopper device; and a control module for the semiconductor chopper devices. The interface device also includes a buffer capacitor having a first end connected to the output converters, and another end, to which a reference voltage is applied, isolated from the network; and a power reserve having an end to be connected to the network and another end connected to the fourth winding.
    Type: Application
    Filed: December 4, 2012
    Publication date: July 18, 2013
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventor: Airbus Operations (SAS)
  • Publication number: 20130180312
    Abstract: A calibration block and method for sensitivity calibration. The calibration block has a curved calibration surface having a central axis and a surface for coupling to a transducer element of an angular scanning phased array ultrasonic testing scanner. The block is configured such that the surface positions the transducer such that its scanning axis is coaxial with the central axis of the curved calibration surface.
    Type: Application
    Filed: January 8, 2013
    Publication date: July 18, 2013
    Applicant: AIRBUS OPERATIONS LIMITED
    Inventor: Airbus Operations Limited
  • Publication number: 20130181374
    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.
    Type: Application
    Filed: January 14, 2013
    Publication date: July 18, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130174918
    Abstract: A bleeding system includes an open conduit and, upstream, a control controlling the hydraulic fluid flow, toward the open conduit. The bleeding system includes a dismountable connection device including connection means adapted to be connected to the bleeding system; an outlet adapted to be connected to a pipe; a first central portion including the connection means, a cylindrical bearing, and a conduit extending from the connection means up to the surface of the cylindrical bearing; and an annular second portion including a bore adapted to pivot on the cylindrical bearing, at least one conduit connecting the outlet and the surface of the bore. The first portion and/or the annular portion include a groove ensuring the hydraulic fluid flows between the conduits. The central portion includes a section arranged between the connection means and the cylindrical bearing to ensure the connection of the connection device to the bleeding system.
    Type: Application
    Filed: March 6, 2013
    Publication date: July 11, 2013
    Applicant: AIRBUS OPERATIONS SAS
    Inventor: Airbus Operations SAS
  • Publication number: 20130170894
    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.
    Type: Application
    Filed: December 7, 2012
    Publication date: July 4, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130168495
    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.
    Type: Application
    Filed: February 7, 2013
    Publication date: July 4, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130157536
    Abstract: An aircraft interior lining component includes a composite material, wherein the composite material includes a matrix, first reinforcing fibres embedded in the matrix and second reinforcing fibres embedded in the matrix. The strength of an interface between a surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fibres is greater than the strength of an interface between a surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres.
    Type: Application
    Filed: February 8, 2013
    Publication date: June 20, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GMBH
  • Publication number: 20130157017
    Abstract: An arrangement for freeing the structures of fail-safe type from the damage tolerance criterion and to allow a significantly improved fatigue resistance, while producing a weight saving. This is provided by forming a composite hybrid structure in a configuration that makes it possible to combine the advantages of metal and of composite material. In a secure hybrid structure, at least two longitudinal structural spars are joined back to back by fastening means. One of the spars is metal and equipped with stability partitions, whereas another spar is made of a composite material with carbon fibers oriented in the direction of the forces to be predicted such that this spar exhibits a rigidity equivalent to that of the metal spar.
    Type: Application
    Filed: December 14, 2012
    Publication date: June 20, 2013
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventor: Airbus Operations (SAS)
  • Publication number: 20130159205
    Abstract: A freight evaluation system for providing freight information with respect to an item of freight of an aircraft includes a freight evaluation unit for collecting and analyzing data of a freight loading system and a recognition system and for determining the current position of the item of freight therefrom.
    Type: Application
    Filed: February 1, 2013
    Publication date: June 20, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130146709
    Abstract: An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage.
    Type: Application
    Filed: December 11, 2012
    Publication date: June 13, 2013
    Applicant: Airbus Operations S.A.S.
    Inventor: Airbus Operations S.A.S.
  • Publication number: 20130146710
    Abstract: An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead.
    Type: Application
    Filed: December 11, 2012
    Publication date: June 13, 2013
    Applicant: Airbus Operations S.A.S.
    Inventor: Airbus Operations S.A.S.