Patents Assigned to Airbus Operations GmbH
  • Patent number: 9393746
    Abstract: A method for the preparation of a dry textile preform for a large surface area fiber-reinforced composite component, in which resin-free textile material layers for purposes of manufacturing the preform are tensioned in each case in a tensioning frame, and in the stretched state are laid down on a moulding body by means of a linear relative movement between the tensioning frame and the moulding body. Also disclosed is a device for the execution of a method of this type with a tensioning frame for purposes of tensioning the material layers, and with a clamping unit for purposes of fixing the laid-down material layers on a moulding body.
    Type: Grant
    Filed: September 15, 2011
    Date of Patent: July 19, 2016
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Christian Luebbering, Hauke Lengsfeld
  • Publication number: 20160200447
    Abstract: A fuel cell system for an aircraft includes at least one fuel cell having a first inlet for providing a fuel, a second inlet for providing an oxidant, an outlet for removing exhaust air and a voltage outlet, an electrically operable hydraulic pump, which is integratable into a hydraulics network of the aircraft and connectable to the voltage outlet of the at least one fuel cell and a controllable hydraulic energy converter with changeable operating behaviour. The hydraulic energy converter is adapted for generating such a power demand in the hydraulics network, that the at least one fuel cell provides a predetermined volume flow of oxygen depleted air at the outlet through delivering electrical power to the hydraulic pump.
    Type: Application
    Filed: December 30, 2015
    Publication date: July 14, 2016
    Applicant: Airbus Operations GmbH
    Inventors: Hauke-Peer Luedders, Sijmen Zandstra, Alexander Fabritz
  • Patent number: 9387920
    Abstract: A cabin structural unit for attaching cabin installation elements is provided for an aircraft. The cabin structural unit is set up in such a way that a cabin installation element is attachable. The cabin structural unit is implemented as self-supporting and fastenable to an aircraft structure.
    Type: Grant
    Filed: April 8, 2009
    Date of Patent: July 12, 2016
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Ulrike Graeber, Peter Grosse-Plankermann, Martin Paetz
  • Patent number: 9389137
    Abstract: A pipe (50) that makes it possible to channel pressurized air into an aircraft, includes an inner tube (52), an outer tube (54) that is essentially coaxial to the inner tube (52), an insulating material (56) that is inserted between the two tubes (52, 54) and that is made of a heat-insulating and gas-porous material, and a leak detection device (70), characterized in that the leak detection device (70) is arranged at least in part between the inner tube (52) and the outer tube (54) and in that at least at one end (60), the detection device follows a concentric trajectory (84) to the inner tube (52).
    Type: Grant
    Filed: July 13, 2012
    Date of Patent: July 12, 2016
    Assignees: AIRBUS OPERATIONS (SAS), AIRBUS OPERATIONS GMBH
    Inventors: Gerard Millet, Xavier Bernard, Matthias Noecker
  • Patent number: 9387935
    Abstract: An aircraft power distribution network comprising first and second galvanically isolated power bus bars, and first and second remote data concentrators (RDCs), each RDC having an input/output interface (I/O) and a power supply, the first RDC power supply being connected to the first power bus bar, the second RDC power supply being connected to the second power bus bar, an input/output device being connected to the I/O of the first RDC and to the I/O of the second RDC, each RDC being adapted to supply electrical power to the input/output device through its respective I/O, wherein each RDC includes a switch for isolating the input/output device, and the switches being operatively coupled such that electrical power cannot be supplied to the input/output device by both RDCs simultaneously. Also, a method of operating the network.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: July 12, 2016
    Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS GMBH
    Inventors: Timothy Todd, Thorsten Nitsche
  • Patent number: 9386825
    Abstract: An aircraft structural component comprising a panel element made of a fiber reinforced composite material and provided with an opening extending fully through the panel element. A reinforcing element made of a fiber reinforced composite material has an opening extending through the reinforcing element from a first surface to a second surface of the reinforcing element. The opening extending through the reinforcing element is aligned with the opening extending through the panel element. A bushing extends through the opening provided in the panel element and the opening provided in the reinforcing element and is adapted to receive an attachment device for attaching a load to the aircraft structural component. A connecting element connects the reinforcing element to the panel element in a region of the panel element adjacent to the opening extending through the panel element by means of a hook and loop connection.
    Type: Grant
    Filed: June 23, 2014
    Date of Patent: July 12, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Hermann Benthien, Axel Soeffker
  • Publication number: 20160193628
    Abstract: A device for sealing a joint includes a body having a bulging inner space, a first opening, in a first portion, from the outside into the inner space for introducing a sealing agent into the inner space, a second opening, at its second end, from the outside into the inner space, wherein the second opening and the inner space are designed such that the body can be positioned over a protruding part of a joint and the protruding part of the joint is completely surrounded by the body.
    Type: Application
    Filed: December 29, 2015
    Publication date: July 7, 2016
    Applicant: Airbus Operations GmbH
    Inventors: Johannes Maslennikov, Sven Chromik
  • Patent number: 9382009
    Abstract: The invention pertains to a relief valve (10) for being arranged on an opening (10) of a fuselage shell of an aircraft, wherein the opening (10) has a front opening edge (9a) and a rear opening edge (9a), and wherein the relief valve (10) features: a cover (13) that is arranged on the fuselage shell by means of an opening and closing device in order to open and close the opening (10) of the fuselage shell, and a prestressing device for prestressing the cover (13) into an initial position, wherein a guide plate (23) is arranged on the cover (13) by means of a mounting device (20), wherein the guide plate is spaced apart from the cover (13) and extends along the cover (13), and wherein the invention furthermore pertains to a fuselage part with such a relief valve (10) for being installed into an aircraft fuselage with a fuselage shell and a plurality of fuselage frames arranged on the inside of the fuselage shell, as well as to an aircraft fuselage with such a fuselage part.
    Type: Grant
    Filed: April 23, 2014
    Date of Patent: July 5, 2016
    Assignee: Airbus Operations GmbH
    Inventor: Juergen Kelnhofer
  • Patent number: 9382005
    Abstract: A cabin segment for a vehicle includes two or more parking spaces, arranged side by side and separated from each other by at least one intermediate wall, for accommodating serving trolleys, and furthermore a vehicle attendant seat which on one side is held on one of the at least one intermediate walls so as to be pivotable on an axis. The vehicle attendant seat is pivotable to an in-use position and to an out-of-the-way position. The in-use position and the out-of-the-way position are situated apart by 90° or more relative to the pivoting of the vehicle attendant seat. This makes possible particularly efficient use of space without having to forego parking spaces or a vehicle attendant seat.
    Type: Grant
    Filed: October 3, 2013
    Date of Patent: July 5, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Ralf Schliwa, Maria Strasdas
  • Patent number: 9382017
    Abstract: A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing a bearing element into the cavity of the aircraft structural component through an opening, which has been formed in the aircraft structural component by the removal of the region of the aircraft structural component having the component fault, in such a way that a bearing surface of the bearing element comes to lie against a region, adjacent to the opening, of an inner surface of the aircraft structural component facing the cavity of the aircraft structural component, fixing the bearing element in its position in the cavity of the aircraft structural component, and closing the opening by means of a repair material.
    Type: Grant
    Filed: December 6, 2011
    Date of Patent: July 5, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Hermann Benthien, Axel Soeffker
  • Patent number: 9381597
    Abstract: Thus relates to a movable backing system for clamping plate-shaped backing work pieces for friction agitation welding and friction stir welding and to a friction agitation or stir welding system. The movable backing system comprises an upper unit to be arranged above the backing work pieces to support the backing work pieces, a lower unit to be arranged below the backing work pieces to support the backing work pieces, and a connecting means connecting the upper and the lower unit to be arranged in a gap between the backing work pieces to be welded.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: July 5, 2016
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Dirk Stermann
  • Patent number: 9376204
    Abstract: A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap.
    Type: Grant
    Filed: April 3, 2013
    Date of Patent: June 28, 2016
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Christoph Winkelmann
  • Patent number: 9376212
    Abstract: An aircraft includes, but is not limited to at least one fuselage with at least one pressurized fuselage region and at least one non-pressurized region and at least one air conditioning system for air conditioning the at least one pressurized fuselage region. The non-pressurized region includes, but is not limited to an air inlet and an air outlet connected to an air source from the pressurized fuselage region. Consequently it is possible to avoid the use of blowers, outlet valves and ram air flaps for ventilating non-pressurized regions of an aircraft.
    Type: Grant
    Filed: January 27, 2011
    Date of Patent: June 28, 2016
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Martin Liebich
  • Patent number: 9380648
    Abstract: A heating system for an aircraft or spacecraft with a control device which includes at least one power line data transmission transceiver and one sensor controller, and at least one remote component which has a sensor element and a heating element, the at least one power line data transmission transceiver being connected to the at least one remote component via a connecting cable, the control device being designed to supply the at least one heating element with power via the connecting cable and the sensor controller being designed to exchange first control signals with the sensor element via the connecting cable.
    Type: Grant
    Filed: November 27, 2012
    Date of Patent: June 28, 2016
    Assignee: Airbus Operations GmbH
    Inventor: Mehmet Altay
  • Patent number: 9377039
    Abstract: A force introduction fitting for lightweight components comprises two radial force introduction faces, at least one axial force introduction face and at least one receiving means for mounting and force introduction of the force introduction fitting. The radial force introduction face and the axial force introduction face enclose a cavity. The radial force introduction face and the axial force introduction face form a one-piece component. A wall is located between the radial force introduction faces and the axial force introduction face, and extends non-parallel to the axial force introduction face, at least in portions, and comprises a bearing face for fitting a retaining face of an anchor part. A force introduction fitting of this type can be produced by using a selective laser melting method. The force introduction fitting can thus be adapted flexibly to loading conditions and has advantageous material properties and a low weight.
    Type: Grant
    Filed: October 18, 2013
    Date of Patent: June 28, 2016
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Claus Emmelmann, Frank-Michael Klaukien, Jannis Kranz, Eric Wycisk, Jan Sassmannshausen
  • Patent number: 9375882
    Abstract: In a method for forming a structural component of an aircraft or spacecraft a preform comprising at least one band is formed by means of braiding around a core. A severing cut is introduced at least in portions into the at least one band of the preform to form two band portions of the at least one band. The two formed band portions of the at least one band are then deformed into a predetermined shape by means of a deformation tool which can be guided along the severing cut. A deformation device is used to carry out the method. A structural component is produced by means of the method and/or the deformation device.
    Type: Grant
    Filed: May 30, 2012
    Date of Patent: June 28, 2016
    Assignee: Airbus Operations GmbH
    Inventor: Marek Beresinski
  • Patent number: 9375781
    Abstract: A riveting device for the riveting of components in an overlap joint, with an upper tool for driving a rivet into a rivet hole passing through the components, and with a lower tool as a dolly, which has a deforming section for purposes of plastically deforming the end of a rivet shaft driven through the rivet hole, wherein the riveting device has a magazine with a feed device for purposes of feeding a rivet into a shot passage of the upper tool, an actuator for purposes of accelerating the rivet introduced into the shot passage of the upper tool in the direction of the components, and an adjustment system for purposes of aligning the shot channel with the rivet hole. Also disclosed is a method for the riveting of components in an overlap joint.
    Type: Grant
    Filed: April 14, 2014
    Date of Patent: June 28, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Robert Alexander Goehlich, Holger Frauen
  • Patent number: 9376210
    Abstract: The invention relates to a cargo handling system for loading and securing one or more freight containers in a cargo hold of an aircraft. The system includes bracket members configured to be secured to a base or floor of the cargo hold, and elongate guide members, each of which is mounted on and interconnects a number of the bracket members arranged in a row, wherein each guide member forms a restraint or a stop against lateral movement of a freight container loaded in the cargo hold. The bracket members include at least one fastening portion configured for tool-less fast-release engagement and locking with a seat track profile in the base or floor of the cargo hold. Furthermore, the bracket members typically extend transversely inwards or inboard of the elongate guide members.
    Type: Grant
    Filed: June 13, 2014
    Date of Patent: June 28, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Ali Lohmann, André Koehler, Johannes Voelker, Christian Grambole, Matthias Ulbrich, Joerg Pump, Soenke Hager
  • Patent number: 9380647
    Abstract: A heating control unit, including a controller housing is provided. The heating control unit includes a microcontroller arranged within the controller housing, with the microcontroller being configured to generate a control signal for a heater and to output the control signal via a control line to the heater. The heating control unit also includes a temperature sensor arranged within the controller housing and coupled to the microcontroller. An active sensor surface of the temperature sensor forms at least part of an outer surface of the controller housing.
    Type: Grant
    Filed: September 24, 2013
    Date of Patent: June 28, 2016
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Thilo Rochell
  • Patent number: D760163
    Type: Grant
    Filed: February 5, 2015
    Date of Patent: June 28, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Stephan Sontag, Magdalena Jobst