Patents Assigned to Airbus Operations GmbH
  • Energy supply network; method and aircraft or spacecraft
    Publication number: 20130307324
    Abstract: An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network.
    Type: Application
    Filed: April 17, 2013
    Publication date: November 21, 2013
    Applicants: Airbus Operations S.A.S., Airbus Operations GmbH
    Inventors: Airbus Operations GmbH, Airbus Operations S.A.S.
  • METHOD AND APPARATUS FOR DETERMINING THE THRUST ON A VEHICLE
    Publication number: 20130311112
    Abstract: A method for determining the thrust of at least one engine, which is held on a supporting structure of a vehicle, includes the steps of acquiring the elongation of at least one structural element onto which the thrust of the at least one engine acts, by means of at least one strain gage; calculating the force causing the elongation in the at least one structural element, taking into account the materials characteristics of the structural element; and determining the thrust of the at least one engine as an effective force component in the direction of thrust of the vehicle. It is thus not necessary to carry out an estimate of the thrust on the basis of other physical variables such as shaft speeds, pressure or exhaust gas temperature of engines.
    Type: Application
    Filed: October 24, 2012
    Publication date: November 21, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: AIRBUS OPERATIONS GMBH
  • Fuselage Segment For A Fuselage Of An Aircraft, Aircraft Fuselage and Aircraft
    Publication number: 20130306793
    Abstract: A fuselage segment for an aircraft fuselage includes a wall with a closed cross section, a first cabin floor, a second cabin floor, and a cargo hold floor. The first cabin floor, the second cabin floor, and the cargo hold floor are vertically spaced apart from each other and connected to the wall. A first passenger region is arranged above the first cabin floor, a second passenger region is arranged above the second cabin floor, and a cargo region is arranged above the cargo hold floor. The cargo region is dimensioned in such a manner that for at least four passenger seats a maximum of 1 m3 of cargo hold volume is provided. In this manner an existing aircraft fuselage can be designed in a demand-oriented manner so that it can accommodate two or more passenger regions.
    Type: Application
    Filed: July 30, 2013
    Publication date: November 21, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Johann Konrad Erben, Sten Kramer
  • AIRCRAFT STRUCTURAL ASSEMBLY
    Publication number: 20130306794
    Abstract: An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft.
    Type: Application
    Filed: February 27, 2013
    Publication date: November 21, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: AIRBUS OPERATIONS GMBH
  • SENSORS FOR LAYOUT VALIDATION OF AN OXYGEN MODULE
    Publication number: 20130305810
    Abstract: A sensor device for an oxygen module mountable on board an aircraft includes an electrical conducting element, a defining device for defining at least one measurement section, assigned to the oxygen module, on the electrical conducting element, and an evaluating unit for determining an electrical resistance present along the at least one measurement section, the evaluating unit further being configured to ascertain, based on the determined electrical resistance, whether the oxygen module is present. An aircraft has at least one oxygen module mounted on board the aircraft and at least one sensor device of the above type.
    Type: Application
    Filed: April 24, 2013
    Publication date: November 21, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: SEBASTIAN UMLAUFT, TOBIAS AMELING, NINO-NINOV PENKOV, ANDREAS HOTTENROTT
  • Aircraft cooling system evaporator arrangement for two independent coolant circuits
    Patent number: 8584485
    Abstract: An aircraft cooling system evaporator arrangement has an evaporation device including four evaporators that are hydraulically separate from each other with respect to coolant flow. Refrigerant flows from a feed line into first and second evaporators, from the first evaporator into and through a third evaporator, and from the second evaporator into and through a fourth evaporator. The first and third evaporators define a first pair of evaporators arranged parallel to a second pair of evaporators defined by the second and fourth evaporators. First and second coolant supply lines of a first coolant circuit supply coolant to one of the evaporators in each of the first and second pair of evaporators respectively, and first and second coolant supply lines of a second, independent coolant circuit supply coolant to the other of the evaporators in each of the first and second pair of evaporators respectively.
    Type: Grant
    Filed: September 1, 2008
    Date of Patent: November 19, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Wolfgang Ebigt, Wilson Willy Casas Noriega
  • Aircraft cooling system evaporator arrangement for two mutually independent coolant circuits
    Patent number: 8584484
    Abstract: An aircraft cooling system evaporator arrangement has at least two mutually independent coolant circuits, at least two evaporation devices arranged to be hydraulically parallel for enabling an exchange of heat between the coolant and a refrigerant, at least two supply lines for supplying refrigerant to the evaporation devices, and at least two discharge lines for discharging refrigerant from the evaporation devices. A different one of the evaporation devices, a different one of the supply lines and a different one of the discharge lines are assigned to each of the coolant circuits, and the supply lines are hydraulically separate from each other as are the discharge lines. At least one refrigerant sensor monitors a refrigerant state of each of the discharge lines and an expansion valve is driven in accordance with the refrigerant sensors to control streams of refrigerant through the supply lines.
    Type: Grant
    Filed: September 1, 2008
    Date of Patent: November 19, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Wolfgang Ebigt, Wilson Willy Casas Noriega
  • Vane having a regulating flap and a gap covering device and an adjusting mechanism for a gap covering device
    Patent number: 8584991
    Abstract: A wing, having an adjustable flap that can be moved between a retracted and an extended setting is provided, as well as a gap-covering device, with an adjustment lever and a gap-covering flap arranged on the latter with a flow surface. The adjustment lever with the gap-covering flap is pre-loaded by means of a pre-loading device into a first setting, in which the gap-covering flap is located in the interior of the wing. The adjustable flap and the adjustment lever with the gap-covering flap are mechanically coupled such that as the adjustable flap moves into its retracted setting, a movement of the adjustment lever takes place against the pre-load effected by the pre-loading device, into a second setting. The flow surface of the gap-covering flap in the second setting of the adjustment lever runs between the upper side of the retracted adjustable flap and the wing flow surface.
    Type: Grant
    Filed: November 10, 2009
    Date of Patent: November 19, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Bernhard Schlipf, Chris Payne, Markus Gibbert, Tom Dostmann
  • Adjustment mechanism of an adjustment device for coupling an adjustment flap to a main wing, and such an adjustment device
    Patent number: 8584992
    Abstract: An adjustment mechanism of a device for coupling a flap to a wing of an aerofoil and for adjusting the flap. The adjustment mechanism includes: a first lever, hinged to the wing via a first rotational joint to form a first axis of rotation; a second lever; a third lever, hingedly coupled to the second lever via a second rotational joint to form a second axis of rotation and hingedly coupled to the flap via a fourth rotational joint; and a push-pull rod, which is connected via a first ball joint to the second lever and via a second ball joint to the flap. The first lever and the second lever are hingedly coupled to one another via a middle joint to form a third axis of rotation. The first, second and third axes of rotation in each position of the flap run through a common pole.
    Type: Grant
    Filed: February 17, 2012
    Date of Patent: November 19, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Bernhard Schlipf, Mirko Missbach
  • Apparatus for preventing fluid spray at leakage areas of a fluid pipe
    Patent number: 8584710
    Abstract: Apparatus for preventing fluid spray at a leakage area of a fluid pipe comprises at least one first enveloping element and at least one second enveloping element which encloses the fluid pipe so as to be flush with it, and which are circumferentially interrupted, wherein the circumferential interruptions of the enveloping elements are arranged so as to be offset relative to each other. In this way, fluid spray formation may be prevented in an economical way. The simple design ensures easy installation and economical production.
    Type: Grant
    Filed: January 5, 2010
    Date of Patent: November 19, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Timo Bruening, Rolf Goessing, Norbert Rostek
  • OPTICAL MEASURING DEVICE WITH A SLIDER AND OPTICAL MEASUREMENT METHOD
    Publication number: 20130300862
    Abstract: An optical measuring device for measuring a surface contour of an object, includes a tripod on which a camera platform is mounted, wherein on the camera platform at least two photo cameras are arranged for imaging the object comprising marking elements, and the at least two photo cameras are arranged on the camera platform in such a manner that imaging the object can be carried out from two different perspectives, wherein between the camera platform and the tripod a displacement device for the linear displacement of the camera platform in three directions that are independent of each other is arranged.
    Type: Application
    Filed: May 7, 2013
    Publication date: November 14, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Andrej Klaas
  • Process for producing a substantially shell-shaped component
    Patent number: 8580170
    Abstract: Disclosed is a process for producing a substantially shell-shaped component, from substantially carbon-fiber-reinforced synthetic material having at least one local reinforcing zone and at least one stiffening element, in particular a fuselage shell, a wing shell, a vertical stabilizer shell or horizontal stabilizer shell of an aircraft or the like. The process according to the invention comprises the following steps: arranging at least one doubler which has already been cured, on an at most partially cured shell skin to form the local reinforcing zone, applying at least one stiffening element which has already been cured, and placing at least one at most partially cured connecting angle bracket against the at least one stiffening element at least in the region of the at least one doubler, and curing the shell skin and the connecting angle bracket.
    Type: Grant
    Filed: June 30, 2006
    Date of Patent: November 12, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Barnaby Law, Kai Schumacher, Jonathon Komadina, Jochen Mueller, Norbert Heltsch
  • System for setting the span load distribution of a wing
    Patent number: 8579237
    Abstract: A system for setting a span load distribution of a wing of an aircraft with a base flap system comprises at least one inboard flap element and one outboard flap element, which elements in the direction of the span are arranged on the trailing edge of the wing, and can be positioned relative to the span direction of the wing. The flap elements are not mechanically coupled with each other and are controlled independently of each other for the purpose of setting the span load distribution.
    Type: Grant
    Filed: August 17, 2005
    Date of Patent: November 12, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Daniel Reckzeh
  • Method for joining a profiled first structural component to a second structural component
    Patent number: 8574391
    Abstract: The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement required for the joining is produced in two parts. In a first step, each precured stringer is covered in advance by a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Vacuum film strips are subsequently arranged in each case on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.
    Type: Grant
    Filed: September 26, 2007
    Date of Patent: November 5, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Peter Sander, Hans Marquardt, Hauke Lengsfeld
  • Force level control for an energy absorber for aircraft
    Patent number: 8573372
    Abstract: A force level control for an energy absorber is provided for aircraft, and includes an adjustment element and a housing, whereby via the adjustment element, a bending radius of the energy absorber element is continuously adjustable in the housing.
    Type: Grant
    Filed: January 31, 2007
    Date of Patent: November 5, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Dirk Humfeldt, Michael Harriehausen, Jan Schroeder, Martin Sperber, Michael Demary
  • Method for measuring and/or testing waviness of a planar textile
    Patent number: 8573035
    Abstract: The invention relates to a method for measuring and/or testing a geometric design parameter, particularly waviness, of a planar textile (10), comprising the steps: disposing the planar textile (10) in an intermediate space (26) between a support (20) and a flexible film (22), applying a differential pressure (?p) between the intermediate space (26) and the environment, so that the film (22) adapts to the planar textile (10), and capturing a surface profile (32) of the film (22).
    Type: Grant
    Filed: September 30, 2009
    Date of Patent: November 5, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Julian Kuntz, Jan Wessels, Frederik Lehners
  • Air conditioning system with hybrid mode bleed air operation
    Patent number: 8572996
    Abstract: An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system and at least one bleed air connection for routing bleed air to the air conditioning system. The electric line network is connected to the air conditioning system and at least one electrical energy source for routing electrical energy to the air conditioning system. The air conditioning system has an electrically operable cooling device. By means of the energy supply system according to the invention the energy withdrawn from the power units is better adapted to the energy necessary for operating the air conditioning system and other systems—such as, for example, wing de-icing—and therefore reduces the excess fuel consumption of the aircraft.
    Type: Grant
    Filed: November 26, 2008
    Date of Patent: November 5, 2013
    Assignees: Airbus Operations GmbH, Airbus S.A.S.
    Inventors: Jan Dittmar, Nicolas Antoine, Uwe Buchholz
  • NOISE REDUCTION UNIT FOR VACUUM SUCTION DRAINS
    Publication number: 20130287505
    Abstract: A noise reduction unit for inserting in a vacuum suction drain is adapted to be flown through by a material to be conveyed through the vacuum suction drain and comprises an inlet section with a first diameter, a middle section with a second diameter and an outlet section with a third diameter. The middle section is adapted to affect a flow velocity reduction of the material to be conveyed such that the noise level arising during the conveying process is being reduced.
    Type: Application
    Filed: April 19, 2013
    Publication date: October 31, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Christian Seibt, Matthias Mueller
  • PASSENGER SERVICE SYSTEM WITH IMPROVED AIR GUIDANCE
    Publication number: 20130286673
    Abstract: A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system, The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (LP) of the passenger service system.
    Type: Application
    Filed: April 23, 2013
    Publication date: October 31, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Sebastian UMLAUFT, Robert Thomas
  • GUIDING MECHANISM FOR OPENING AND CLOSING A CARGO DOOR OF AN AIRCRAFT, AIRCRAFT WITH SUCH A GUIDING MECHANISM AND METHOD FOR OPENING AND CLOSING A CARGO DOOR OF AN AIRCRAFT
    Publication number: 20130284855
    Abstract: A guiding mechanism is disclosed for moving a cargo door into extended cargo door positions to open and into a retracted cargo door position to close at least one section of an opening of a loading hatch on a fuselage of an aircraft. A first structural component in the form of the cargo door is pivotably supported on a second structural component on a front lateral edge by a pivot joint arranged in a pivoting axis in order to assume the extended cargo door positions on the loading hatch. The guiding mechanism features at least one actuator for moving the cargo door, a supporting device arranged on an actuating element, and a spring mechanism on the actuator for exerting a compressive force.
    Type: Application
    Filed: October 18, 2012
    Publication date: October 31, 2013
    Applicant: Airbus Operations GmbH
    Inventor: Airbus Operations GmbH