Patents Assigned to Airbus Operations
  • Structural component and method for producing a structural component
    Patent number: 9988136
    Abstract: A structural component for reinforcing the fuselage of an aircraft or spacecraft is integrally formed and segmented into surface-like stiffening sections, whereby at least one stiffening section is formed as a rigid mesh section, and at least one stiffening section is formed as a solid section.
    Type: Grant
    Filed: October 29, 2015
    Date of Patent: June 5, 2018
    Assignee: Airbus Operations GmbH
    Inventors: Memis Tiryaki, Michael Sauer
  • Composite structural member
    Patent number: 9987823
    Abstract: A method of manufacturing a composite structural member including laying up a stack of fiber reinforced laminate plies, wherein at least one of the plies is laid up as discrete first and second ply portions, and the fibers of the second portion have a different characteristic from those of the first portion. Also, a composite structural member manufactured according to the method.
    Type: Grant
    Filed: October 26, 2015
    Date of Patent: June 5, 2018
    Assignee: Airbus Operations Limited
    Inventors: Matthew Eli Eli, David Brian, Enzo Cosentino, I, James Lloyd, Filipe Almeida, Christopher David Burleigh
  • Wing for an aircraft, and an aircraft comprising such a wing
    Patent number: 9988142
    Abstract: A wing for an aircraft, including a main wing and a wing tip device, a front blade and a rear blade of the wing tip device extending from an attachment end, a front blade leading edge extending in front of a rear blade leading edge and a front blade trailing edge extending in front of a rear blade trailing edge, in a chord direction, and at a front blade tip the front blade extending under a different dihedral angle than the rear blade at a rear blade tip. The front blade leading and trailing edges, as well as the rear blade leading and trailing edges have a tangent-continuous developing. The front blade leading edge extends tangent-continuously with the wing leading edge. The rear blade trailing edge extends tangent-continuously with the wing trailing edge. The front blade trailing edge extends behind the rear blade leading edge, in the chord direction.
    Type: Grant
    Filed: March 15, 2017
    Date of Patent: June 5, 2018
    Assignee: Airbus Operations GmbH
    Inventor: Gerd Heller
  • AIRCRAFT HAVING A DRAG COMPENSATION DEVICE BASED ON A BOUNDARY LAYER INGESTING FAN
    Publication number: 20180148162
    Abstract: An aircraft includes a fuselage having a tapered rear shape, a landing gear for moving the aircraft on a runway, a wing attached to the fuselage, at least a main engine for providing a main thrust and a rear fan, wherein the rear fan is attached to a tail section of the fuselage, wherein the aircraft is designed for conducting a take-off rotation around the landing gear during take-off from the runway, such that the tail section of the fuselage approaches the runway, wherein the rear fan is an open fan having fan blades extending in a radial direction to a longitudinal axis of the fuselage, wherein the fan blades are dimensioned to equal at least a boundary layer thickness of the flow along the fuselage and to be smaller than the gap between the runway and the tail section of the fuselage during the take-off rotation.
    Type: Application
    Filed: November 22, 2017
    Publication date: May 31, 2018
    Applicant: Airbus Operations GmbH
    Inventor: Bernd Trahmer
  • CONSTRUCTION GROUP FOR AN AIRCRAFT FOR FEEDING A LINE TO A CABIN MODULE
    Publication number: 20180148171
    Abstract: A construction group of an aircraft for feeding a line to a connector section of the cabin module includes a flex zone for providing of at least one cabin module having a connector section for physical connection to a line of the aircraft. The flex zone is configured to receive different cabin modules and/or a cabin module at different positions. The construction group further includes a guide element for guiding the line to be connected to the connector section along the fuselage of the aircraft, and a support element extending along the flex zone for feeding the line from the guide element to the connector section, wherein during the receiving of the construction group in the aircraft, the longitudinal axis of the support element includes a component in direction of the attitudinal axis of the aircraft.
    Type: Application
    Filed: November 14, 2017
    Publication date: May 31, 2018
    Applicant: Airbus Operations GmbH
    Inventors: Sebastian Scheffler, Anja Wessels, Malte Fuerstenberg, Benjamin Klotz, Olaf Glaesker, Zoltan Czudar, Ines Dittmann, Bernd Kazmeier
  • Electrical energy distribution network in a transport vehicle, such as an aircraft, and an electrical installation in an aircraft
    Patent number: 9983609
    Abstract: An electrical energy distribution network in a transport vehicle, such as an aircraft, includes nodes to which at least one power supply source and at least one equipment can be connected by external links. The nodes are interconnected by internode links forming at least one mesh in a meshed network, each mesh being polygonal of order higher than or equal to three, at least one node of each mesh being an active node controlled by a management unit. The active nodes include switches and transmit physical operating characteristics measurements to the management unit, which configures the active nodes according to said measurements so as to enable each equipment to receive power supply via the meshed network. Flexibility in configuration of the electrical energy distribution network is thus achieved.
    Type: Grant
    Filed: November 10, 2014
    Date of Patent: May 29, 2018
    Assignees: Airbus (SAS), Airbus Operations (S.A.S.)
    Inventors: Catalin Perju, Claude Cuiller, Kathryn Waidelich, Xavier Valancogne, Hervé Le-Flecher, Damien Valentin
  • Method and system to verify the calibration of a system for non-destructive testing
    Patent number: 9983174
    Abstract: A method and assembly for verification of the calibration of a system for non-destructive testing of pieces. The assembly includes an ultrasound probe, a perfect reflector having reference defects, and recording and data processing units. The ultrasound probe scans the perfect reflector and ultrasonic reflections from the reflector are measured by the non-destructive testing system, a recording unit records the measurements, and a data processing unit forms a virtual map of the perfect reflector based on the amplitude and time of flight of the reflections and based on predetermined characteristics of the material of the reflector.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: May 29, 2018
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Franck Bentouhami
  • Method and aircraft server system for communication with a personal electronic device in an aircraft
    Patent number: 9986037
    Abstract: An aircraft server system includes a wireless transceiver configured to wirelessly emit and receive radio frequency signals in the passenger cabin of an aircraft, and a plurality of virtual network server units, each configured to remotely control one or more virtual network clients on one of a plurality of personal electronic devices, PEDs, wirelessly connected to the aircraft server system.
    Type: Grant
    Filed: October 23, 2014
    Date of Patent: May 29, 2018
    Assignee: Airbus Operations GmbH
    Inventors: Hans-Achim Bauer, André Zybala
  • SELF-PERFORATING SPACER FOR AN INSULATION BLANKET OF AN AIRCRAFT, ASSEMBLY METHOD FOR SAID SPACER AND INSULATION BLANKET FOR AN AIRCRAFT FITTED WITH SAID SPACER
    Publication number: 20180141635
    Abstract: A self-perforating spacer has a first part and a second part, the first part including a through-seat, the first and second parts being designed to be assembled together and the self-perforating spacer including a cutting system that cuts when the self-perforating spacer is assembled. A method for assembling a self-perforating spacer on an insulation blanket and an insulation blanket fitted with at least one self-perforating spacer is also described.
    Type: Application
    Filed: November 13, 2017
    Publication date: May 24, 2018
    Applicant: Airbus Operations S.A.S.
    Inventors: Christian Nguyen, Arnaud D'Ouince, Serge Blind, Gerard Millet, Thomas Menage
  • Fluid actuator for influencing the flow along a flow surface, as well as blow-out device and flow body comprising a like fluid actuator
    Patent number: 9976580
    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: Grant
    Filed: March 27, 2013
    Date of Patent: May 22, 2018
    Assignee: Airbus Operations GmbH
    Inventors: Matthias Lengers, Ulrich Scholz
  • Inspection methods and systems for detecting leaks in vacuum bag assemblies
    Patent number: 9976926
    Abstract: Inspection methods and systems for detecting leaks in a vacuum bag assembly used in the manufacture of a composite part based on spraying helium over the vacuum bag and detecting the helium drawn by the vacuum inside the vacuum bag through a leak. The inspection methods comprise creating a local helium atmosphere in a chamber over the vacuum bag assembly by zones, following a programmed zonal sequence, for a first leak detection test of each zone and a subsequent second leak detection test if the first test gives a positive result. The inspection systems comprise a helium spraying system and helium detecting equipment arranged to implement the inspection methods.
    Type: Grant
    Filed: May 25, 2016
    Date of Patent: May 22, 2018
    Assignee: Airbus Operations S.L.
    Inventors: Georgina Galera Córdoba, Augusto Pérez Pastor, Francisco Javier Jordán Carnicero, Yolanda Miguez Charines, Ángel Pablo Gordo Arias, Laura Álvarez Antoñón
  • AIRCRAFT SEAT KIT, AND AIRCRAFT SEAT AND CABIN ARRANGEMENT WITH DIFFERENT TYPES OF SEAT RAIL ADAPTERS
    Publication number: 20180134394
    Abstract: An aircraft seat kit with one aircraft seat, and an aircraft seat and cabin arrangement with at least two aircraft seats for being mounted one after the other onto a seat rail are described. The seat rail provides a grid with a pre-determined grid pitch for mounting the at least two aircraft seats. Each of the at least two aircraft seats includes: a seating structure, a support for supporting the seating structure, and one of two types of seat rail adapters for mounting the support onto the seat rail. The two types of seat rail adapters differ from each other in that they configure at least one aircraft seat with a different distance in a longitudinal direction between a seat reference point and a reference mounting position, respectively.
    Type: Application
    Filed: November 7, 2017
    Publication date: May 17, 2018
    Applicant: Airbus Operations GmbH
    Inventor: Jörg Weifenbach
  • Information system comprising a screen and corresponding computers, cockpit and aeroplane
    Patent number: 9971559
    Abstract: An information system comprising a first computer and a second computer, a first display screen and a display management device connected to the first screen. Each computer communicates with the display management device by means of a communication network. The display management device allows control of the display of information from the first computer or from the second computer on the first display screen. A tactile unit is applied to the first display screen and an additional communication network, which is separate from the communication network between each computer and the display management device, allows the tactile unit to communicate with the second computer so that a user is easily able to act on the information displayed on the first screen without the risk of interference with the rest of the system.
    Type: Grant
    Filed: March 3, 2016
    Date of Patent: May 15, 2018
    Assignee: Airbus Operations (SAS)
    Inventors: Jean Monfraix, Rui Fernandes Dos Santos, Mathieu Collignon, Arnaud D'Andrea
  • Rotary joint with actuator, framework construction kit and framework with rotary joints
    Patent number: 9970190
    Abstract: A rotary joint includes a socket rod having a socket rod flange with a basically spheroid con-cave bearing surface at a first end, a housing nut encircling the socket rod and having a threaded wrenching head, a ball rod having a basically spheroid convex bearing surface and threaded side walls around the convex bearing surface, and a joint actuator configured to actuate relative movement of the socket rod flange and the ball rod. A diameter of the threaded side walls of the ball rod corresponds to a diameter of the threaded wrenching head of the housing nut.
    Type: Grant
    Filed: October 19, 2016
    Date of Patent: May 15, 2018
    Assignee: Airbus Operations GmbH
    Inventors: Hermann Benthien, Matthias Hegenbart, Andreas Poppe
  • Lining Panel And Method For Manufacturing Lining Panel
    Publication number: 20180127100
    Abstract: A lining panel having a panel element, a rectangular through hole and a flap is provided. The lining panel has a flap which is rotatable about a hinge integrated into the panel element in order to open and/or close the rectangular through hole. A fuselage element for an aircraft includes such a lining panel.
    Type: Application
    Filed: November 7, 2017
    Publication date: May 10, 2018
    Applicant: Airbus Operations GmbH
    Inventor: Ingo Roth
  • Lightweight structural panel
    Patent number: 9963218
    Abstract: What is described is a lightweight structural panel which comprises a planarly extended outer skin of given thickness and stiffening elements which are connected to this outer skin and are arranged at a given distance from one another. According to the invention, the outer skin is formed by component layers which are each extended in the planar direction of the lightweight structural panel and complement one another in the direction of thickness to form the thickness of the outer skin and are interconnected, the stiffening elements being formed in one piece with one of the component layers.
    Type: Grant
    Filed: April 22, 2016
    Date of Patent: May 8, 2018
    Assignee: Airbus Operations GmbH
    Inventor: Alexei Vichniakov
  • Airfoil portion with a chamber
    Patent number: 9963219
    Abstract: An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described.
    Type: Grant
    Filed: September 1, 2015
    Date of Patent: May 8, 2018
    Assignees: Airbus Defence and Space GmbH, Airbus Operations GmbH
    Inventors: Michael Meyer, Wolfgang Machunze, Matthias Lengers
  • Auxiliary power unit starting system for an aircraft
    Patent number: 9964044
    Abstract: An auxiliary power unit (APU) starting system for an aircraft comprises an APU comprising a starter motor and a generator, a DC power network, an AC power network, an electric connection line, and a control unit for controlling the APU starting and generating phase. The APU starting system additionally comprises switches for alternatively connecting through the electric connection line the DC power network with the APU starter motor, and the AC power network with the APU generator, wherein the control unit is further configured to operate the switches to connect the DC power network with the APU starter motor during the APU starting phase, and the AC power network with the APU generator during the APU starting phase.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: May 8, 2018
    Assignee: Airbus Operations S.L.
    Inventors: Alberto Juarez Becerril, Mario Marcos Garcia
  • METHOD AND DEVICE FOR MANAGING CONFIGURATIONS OF AN AIRCRAFT
    Publication number: 20180118372
    Abstract: The device for assisting the landing of an aircraft in a phase of descent for the purpose of a landing on a runway with the help of an instrument landing assistance module includes an image capturing module for capturing a sequence of successive images of the ground, an image processing module, a monitoring module for detecting on the processed images at least one visual characteristic corresponding to a runway, a computation module for computing a current position of the aircraft and a comparison module for comparing the computed current position with a signal representative of a current position of the instrument landing assistance module, a go-around warning being transmitted to a display unit, if the current positions are not substantially identical.
    Type: Application
    Filed: October 18, 2017
    Publication date: May 3, 2018
    Applicant: Airbus Operations S.A.S.
    Inventors: Josep Boada-Bauxell, Fabrice Bousquet
  • SEAT RAIL ADAPTER COMPRISING TWO MOUNTING PARTS, SEAT RAIL AND CABIN ARRANGEMENT COMPRISING SUCH A SEAT RAIL ADAPTER
    Publication number: 20180118056
    Abstract: A seat rail adapter for flexibly mounting an object onto a seat rail, a seat arrangement and a cabin arrangement with same are described. The seat rail has a U-shaped profile with a lower flange, two web portions, two upper flanges, a gap between the upper flanges, and a cavity inside the seat rail. The seat rail adapter includes two mounting parts capable of being inserted through the gap into the cavity inside the seat rail, such that, when inserted, a hook portion of each of the mounting parts is engaged with the cavity, and a shaft portion of each of the two mounting parts extends through the gap to outside the seat rail. Further, the shaft portions include a rounding so as to allow insertion of one mounting part into the cavity by a swivel movement, when the other mounting part is already inserted therein.
    Type: Application
    Filed: October 16, 2017
    Publication date: May 3, 2018
    Applicant: Airbus Operations GmbH
    Inventor: Carsten Wolgast