Patents by Inventor AIRBUS OPERATIONS GMBH

AIRBUS OPERATIONS GMBH 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: 20140138480
    Abstract: A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.
    Type: Application
    Filed: March 15, 2013
    Publication date: May 22, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: AIRBUS OPERATIONS GMBH
  • Publication number: 20140090802
    Abstract: 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: Application
    Filed: March 29, 2013
    Publication date: April 3, 2014
    Applicant: Airbus Operations GMBH
    Inventor: Airbus Operations GMBH
  • Publication number: 20140084111
    Abstract: A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft.
    Type: Application
    Filed: May 10, 2013
    Publication date: March 27, 2014
    Inventors: Airbus Operations GmbH, Airbus SAS
  • Publication number: 20140061387
    Abstract: A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated.
    Type: Application
    Filed: March 26, 2013
    Publication date: March 6, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: AIRBUS OPERATIONS GMBH
  • Publication number: 20140050884
    Abstract: Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part.
    Type: Application
    Filed: January 16, 2013
    Publication date: February 20, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20140027088
    Abstract: A heat exchanger for cooling air, with a coolant onward-flow connection for feeding liquid coolant for cooling air and a coolant return-flow connection for discharging liquid coolant. For removing ice by melting accumulated ice in the heat exchanger, a heater is provided that is associated with an electrical heating element. An operational safety device prevents overheating of the heater. The operational safety device comprises a fault-current detection device. Such a heater, with a heating element for heating air for subjecting accumulated ice to heated air, and with such an operational safety device is provided. Also, a galley for a commercial aircraft is provided with a receiving space for trolleys, and a cooling device for cooling the receiving space. The cooling device comprises such a heat exchanger for cooling air.
    Type: Application
    Filed: January 25, 2013
    Publication date: January 30, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20140021304
    Abstract: A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid.
    Type: Application
    Filed: October 12, 2012
    Publication date: January 23, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20140007702
    Abstract: A measurement device for measurement of forces in structural components, having a measurement sensor, which is embodied such that it is connected with the structural component in a force-fit and/or form-fit manner, and generates measurement signals as a function of force transfers in the structural component, the measurement device having a measurement casing upon the measurement sensor. Processing of received measurement signals can occur, and the measurement casing has connecting means, for placing in position and releasable attachment of the measurement casing on the structural component, and the contacting means of the measurement casing can establish contact with the measurement sensor for the reception of the measurement signals.
    Type: Application
    Filed: December 21, 2012
    Publication date: January 9, 2014
    Applicant: Airbus Operations GmbH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130343805
    Abstract: The present invention provides a structural element for an aircraft and spacecraft, having a core which includes core regions which are uncoupled from one another by means of an expansion joint arranged between the core regions. The present invention further provides a method for producing a structural element for an aircraft or spacecraft, including the following method steps: providing a core of the structural element, which core includes core regions; and arranging an expansion joint between the core regions. The present invention relates still further to an aircraft and/or spacecraft having such a structural element.
    Type: Application
    Filed: May 7, 2013
    Publication date: December 26, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: AIRBUS OPERATIONS GMBH
  • Publication number: 20130334289
    Abstract: A movable joining device for connecting structural components of an aircraft, with joining means moveably arranged on a guiding device situated on the outside of the structural components so as to fixedly connect joining edges of the structural components positioned adjacent to each other, wherein the joining means includes a welding unit that can move on the rail-like guiding device, and is equipped with a special so-called bobbin tool as a tool for friction stir welding.
    Type: Application
    Filed: October 5, 2012
    Publication date: December 19, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130320150
    Abstract: A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.
    Type: Application
    Filed: March 27, 2013
    Publication date: December 5, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: AIRBUS OPERATIONS GMBH
  • 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.
  • 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
  • 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
  • Publication number: 20130306797
    Abstract: To save weight and to enhance safety, a hydrogen tank for supplying an engine with hydrogen is attached externally to an aircraft.
    Type: Application
    Filed: January 28, 2013
    Publication date: November 21, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130304312
    Abstract: Diagnostic system including a sensor device with a sensor for generating signals corresponding to a first operational condition, a control device with a timer and function for performance of measurements, and a signal transmission device. The system includes a device for determination of a second operational condition of the system component and configured where the sensor value of the signal transmission device corresponding to the first operational condition is furnished when the sensor value corresponding to a second operational condition of the transmission mechanism is higher or lower than a comparative value, and housing component of a lubricant container and in particular closure device for sealing an opening of such a housing component from a lubricant which is present in the operational use thereof in an internal space thereof, having arranged therein: at least one sensor device comprising at least one sensor for determining the water content in the lubricant.
    Type: Application
    Filed: April 19, 2013
    Publication date: November 14, 2013
    Inventor: Airbus Operations GmbH
  • Publication number: 20130291981
    Abstract: The invention relates to a fluid actuator for influencing the flow along a flow surface by ejection of a fluid. By means of a like fluid actuator a continuous flow is distributed to at least two outlet openings in order to generate fluid pulses out of these outlet openings. Control of this distribution takes place inside an interaction chamber supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which respective different pressures may be applied. The flow in the interaction chamber is distributed to the individual outlet openings as a function of the pressure difference at the control openings.
    Type: Application
    Filed: March 27, 2013
    Publication date: November 7, 2013
    Inventor: Airbus Operations GmbH
  • 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
  • Publication number: 20130277495
    Abstract: A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.
    Type: Application
    Filed: April 2, 2013
    Publication date: October 24, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130277502
    Abstract: A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.
    Type: Application
    Filed: April 12, 2013
    Publication date: October 24, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH