Patents Assigned to Airbus Operations S.A.S.
  • Publication number: 20190251852
    Abstract: A decision aid system includes an acquiring module for acquiring at least one current flight parameter of the aircraft, a reception module for receiving a set of information comprising runway characteristic data concerning at least the landing runway on which the aircraft is likely to land, an estimation module for estimating at least one likelihood of at least one state in which the aircraft can be upon the landing, an estimation module for estimating at least one probability of transition between the state or states estimated by the estimation module, an assessment computation module for in-flight assessment of at least one landing distance likely to be travelled by the aircraft on the landing runway, a determination module for determining at least one landing recommendation, a sending module for sending a signal representative of the landing recommendation or recommendations to a user device.
    Type: Application
    Filed: January 30, 2019
    Publication date: August 15, 2019
    Applicant: Airbus Operations S.A.S.
    Inventor: Fabien Moll
  • Patent number: 10380903
    Abstract: Collision avoidance method and device for an aircraft formation relative to an intrusive aircraft. The device manages a collision avoidance for an aircraft formation, relative to an aircraft external to the aircraft formation, the aircraft formation comprising a lead aircraft and at least one following aircraft, the device comprising a formation flight management unit with which all the aircraft of the aircraft formation are equipped and configured to manage the formation flight thereof, and management and control assemblies for determining and applying a coordinated avoidance maneuver intended for all the aircraft of the aircraft formation, this coordinated avoidance maneuver being determined so as to make it possible to avoid the collision with the intrusive aircraft while maintaining the formation flight.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: August 13, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Jean-luc Robin, Camille Caruhel, Sylvain Deplanche
  • Patent number: 10377463
    Abstract: An aircraft having a hatch and a fall-protection device includes a structure comprising a roof pierced with an opening, a cover plate, and a lock provided to adopt a locking position, in which the lock holds the cover plate in the closed position in the opening, or, alternatively, an unlocked position, in which the lock does not hold the cover plate. The aircraft further comprises at least one fall-protection device provided so that, when the lock moves into the unlocked position, it is in a first position to allow movement of the cover plate under the influence of gravity from its closed position to an intermediate position, in which the cover plate is suspended from the structure and then moves from the first position into a second position, during which movement the cover plate moves from the intermediate position into an open position, no longer attached to the structure.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: August 13, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Yannick Chourreau, Loic Challancin
  • Patent number: 10360741
    Abstract: The disclosure herein proposes identifying precursors to all the phenomena which can have an impact on the service use of an aircraft. It relates to a system for predicting failures in an aircraft, including a processor configured to analyze a current behavior of at least one flight parameter of the aircraft to detect any deviation of the current behavior relative to a predetermined behavior model of the parameter, the behavior model being determined from a plurality of series of learning data relating to the parameter collected during the flights of a set of aircraft.
    Type: Grant
    Filed: May 26, 2017
    Date of Patent: July 23, 2019
    Assignees: Airbus Operations (S.A.S), Airbus (S.A.S.)
    Inventors: Jean-Max Huet, Franck Duluc, Eric Benhamou, Bruno Maillard
  • Patent number: 10358204
    Abstract: A joint assembly in an aircraft connecting a belly fairing to the fuselage of the aircraft. The belly fairing has a sewing angle connected to a main belly fairing section, while the fuselage has a fuselage skin with an exterior and an interior. The joint assembly includes a sewing angle with a flange connected to the fuselage skin exterior at a fixation zone of the fuselage skin, with the fixation zone being overlapped by the flange where it is connected thereto. The joint assembly further includes a stringer connected to the fuselage skin interior and overlapping the fixation zone. This joint assembly is less susceptible to vibrations. The disclosure herein also pertains to a method of providing such a joint assembly.
    Type: Grant
    Filed: December 28, 2015
    Date of Patent: July 23, 2019
    Assignee: Airbus Operation (S.A.S.)
    Inventors: François Rouyre, Christian Cros, Jérome Antypas, Sébastien Menard
  • Patent number: 10358226
    Abstract: In order to bring a turbofan engine closer to the lower surface of a wing box, the disclosure herein foresees an assembly for an aircraft including a mount for mounting a rigid structure of an engine strut to the wing box, the mount including an upper wing mount including a fitting secured to the upper surface of the wing box.
    Type: Grant
    Filed: May 4, 2016
    Date of Patent: July 23, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Olivier Pautis
  • Patent number: 10358206
    Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: July 23, 2019
    Assignees: Airbus Operations, S.L., Airbus Operations (S.A.S.)
    Inventors: Javier Toral Vázquez, Diego Folch Cortes, Esteban Martino González, Pablo Goya Abaurrea, Vasillis Votsios, Michel Fouinnetau, Sylvain Roumegas
  • Patent number: 10351254
    Abstract: An aircraft engine pylon includes two side panels and an upper stringer and a lower stringer assembled to form a strut assembly extending in a longitudinal direction (AX) corresponding to the direction in which the aircraft is moving and an internal reinforcement structure including a plurality of reinforcements. The pylon also includes a reinforcement zone on each side panel and a front housing to receive a main front center reinforcement and a rear housing to receive a main rear center reinforcement.
    Type: Grant
    Filed: October 13, 2016
    Date of Patent: July 16, 2019
    Assignee: Airbus Operations S.A.S.
    Inventors: Frederic Journade, Eric Bouchet, Gerard Coudouent, Bogdan Sina, Romain Terral, Sylvain Cros, Jerome Puech, Cyrielle Rogeron
  • Patent number: 10356009
    Abstract: Multiple-core processor to be connected, by way of communication ports, to a deterministic switched Ethernet network using virtual links to which items of equipment are connected, the processor including clusters each including cores, wherein at least one cluster of the processor implements a switch function that makes it possible to interconnect the items of equipment in the network. At least one cluster of the processor implements an end system function providing functions of sending and receiving data in the network, and at least one cluster of the processor implements an application.
    Type: Grant
    Filed: September 25, 2017
    Date of Patent: July 16, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Adrien Gauffriau, Benoît Triquet
  • Patent number: 10352739
    Abstract: A measurement device can be attached to an outer wall of a movable object or of a stationary object arranged in a flow of air in order to measure physical quantities. The measurement device includes a mounting which has recesses having an opening leading to the outside, sensors being provided in said recesses. The device includes a cavity into which the recesses lead and which contains a flexible printed circuit, to which the sensors are connected. The method for manufacturing such a device includes the following steps: attaching sensors to the flexible printed circuit; and attaching the flexible printed circuit provided with sensors to the mounting, the sensors being inserted into the recesses and the circuit being inserted into the cavity.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: July 16, 2019
    Assignee: Airbus Operation S.A.S.
    Inventors: Nicolas Dupe, Olivier Sornique
  • Publication number: 20190210714
    Abstract: An aerodynamic element is provided with at least one set of protruding elements, each of the protruding elements is produced in the form of an elongate and profiled rib projecting from a surface of the aerodynamic element. The protruding elements are arranged at the surface of the aerodynamic element, one beside the other, being oriented substantially parallel to one another so that each of them generates a vortex, the set of vortices thus generated making it possible to reduce crossflow instability.
    Type: Application
    Filed: January 4, 2019
    Publication date: July 11, 2019
    Applicant: Airbus Operations S.A.S.
    Inventor: Mathias Farouz-Fouquet
  • Patent number: 10345097
    Abstract: A strain measurement method and device are provided. The strain measurement device includes at least one filiform strain sensor and a support of longilinear shape on which the filiform strain sensor is positioned. The strain measurement device also includes a stiffener.
    Type: Grant
    Filed: July 29, 2016
    Date of Patent: July 9, 2019
    Assignee: AIRBUS OPERATIONS S.A.S.
    Inventors: Marc Sartor, Patricia Morgue, Manuel Paredes
  • Patent number: 10348633
    Abstract: The disclosure herein proposes minimizing the processing and transmission time of an urgent message from an aircraft and relates to a communication system of an aircraft including a set of communication devices or systems intended to transmit data streams, the system including a data processing interface configured to transmit a data stream by dividing it into several data packets and by making the data packets simultaneously pass through different communication devices or systems from among the set of communication devices or systems.
    Type: Grant
    Filed: November 30, 2015
    Date of Patent: July 9, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Luc Emberger, Julie Facon
  • Patent number: 10343768
    Abstract: An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing gear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: July 9, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Daniel Bellet, Guillaume Gallant, François Loyant, Alexandre Legardez, Simon Roux
  • Patent number: 10345327
    Abstract: A method and device for estimating the airspeed of an aircraft includes a first estimation unit configured to estimate the airspeed of the aircraft according to a first estimation method, a second estimation unit configured to estimate the airspeed of the aircraft according to a second estimation method, a weighting unit configured to weight the two airspeeds estimated by the first and second estimation methods and a computation unit configured to sum the weighted airspeeds so as to obtain an estimated airspeed of the aircraft.
    Type: Grant
    Filed: November 20, 2015
    Date of Patent: July 9, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Martin Delporte
  • Patent number: 10347143
    Abstract: A collision avoidance method and system for a trailer aircraft of an aircraft formation relative to an intruder aircraft. The collision avoidance system is embedded in a trailer aircraft of an aircraft formation and it is intended to avoid a collision relative to at least one aircraft external to the aircraft formation, called intruder aircraft, the aircraft formation including a lead aircraft and the at least one trailer aircraft, the collision avoidance system being configured to bring the trailer aircraft to a safety point dependent on a safety zone, prior to the implementation of an avoidance maneuver, the safety zone corresponding to a zone located to the rear of the lead aircraft and with no wake turbulence generated by the lead aircraft.
    Type: Grant
    Filed: April 19, 2017
    Date of Patent: July 9, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Jean-luc Robin, Camille Caruhel, Sylvain Deplanche
  • Patent number: 10336460
    Abstract: An acoustic panel for an aircraft nacelle includes a cellular layer configured to trap noise, a backplate fixed to one surface of the cellular layer and a facesheet fixed to another, opposite, surface of the cellular layer. The facesheet includes a layer of a preimpregnated woven material containing weft yarns spaced apart from one another and warp yarns spaced apart from one another so that the facesheet exhibits openings between the yarns.
    Type: Grant
    Filed: March 24, 2017
    Date of Patent: July 2, 2019
    Assignee: Airbus Operations S.A.S.
    Inventors: Florian Ravise, Hassan Menay
  • Patent number: 10336458
    Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: July 2, 2019
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Julien Guillemaut, Sébastien Alby, Jérôme Colmagro, Pascal Pome, Jonathan Blanc, Thomas Robiglio, Tobias Sjostrom
  • Publication number: 20190197906
    Abstract: A piloting aid system for ensuring the availability an automatic pilot corresponding to an automatic piloting system and/or a flight director and/or a thrust regulation device to be controlled as a function of a speed information item determined from a source of information, and configured to operate according to a first current guidance mode and an approach capability that are part of a first set of guidance modes and approach capabilities. The system includes a surveillance module to be able to detect the loss of sources of information, a module for determining a second set of guidance modes and of approach capabilities as a function of the source or sources of information whose loss was detected by the surveillance module, a module for use, by the automatic pilot and/or the thrust regulation device, of a second current guidance mode and an approach capability that are part of the second set.
    Type: Application
    Filed: December 4, 2018
    Publication date: June 27, 2019
    Applicant: Airbus Operations S.A.S.
    Inventors: Thierry Bourret, Matthieu Barba, Maxime Semat, Florent Lanterna, Didier Sauve
  • Publication number: 20190196508
    Abstract: A piloting assistance system for an aircraft includes a measuring module for measuring a vertical manoeuvre of the aircraft, a computational module for computing a first load factor from the measured vertical manoeuvre and from a setpoint vertical manoeuvre, a measuring module for measuring an inclination angle, a pitch rate and a pitch acceleration, a protection module including a computational submodule configured to compute a second load factor and a comparison submodule in order to compare the first and the second load factor in order to determine an applicable load factor equal to the minimum between the first and the second load factor, a computational module configured to compute elevator control from the applicable load factor and a sending module configured to send the elevator control to the automatic pilot.
    Type: Application
    Filed: December 4, 2018
    Publication date: June 27, 2019
    Applicant: Airbus Operations S.A.S.
    Inventors: Matthieu Barba, Maxime Semat, Florent Lanterna