Patents Assigned to Airbus Operations S.A.S.
  • Publication number: 20200070949
    Abstract: A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.
    Type: Application
    Filed: August 29, 2019
    Publication date: March 5, 2020
    Applicant: Airbus Operations S.A.S.
    Inventors: Alain Porte, Jacques Lalane
  • Publication number: 20200070992
    Abstract: A central fairing of a pylon of an aircraft including: at least one opening to allow access to beneath the central fairing, an articulated panel that is able to move between a closed position in which the articulated panel blocks the opening and an open position in which the articulated panel at least partially frees the opening, at least one articulation for permanently connecting the articulated panel to at least one fixed element, and—at least one locking system for holding the articulated panel in the closed position. Since the articulated panel is always connected to the aircraft, it can be made larger since it is no longer carried by the operator. Consequently, the opening can be blocked with a single articulated panel.
    Type: Application
    Filed: August 13, 2019
    Publication date: March 5, 2020
    Applicant: Airbus Operations S.A.S.
    Inventor: Thierry Theron
  • Patent number: 10578636
    Abstract: An electronic device for detecting an air flow includes at least one sensor having a pair of platelets, each platelet having an RTD and having one end fixed, the other end being free and overlapping the free end of the other platelet. A platelet is flexible so as to form a switch for an electrical circuit. An air flow with a speed higher than a predetermined speed makes the sensor go from a first state, corresponding to a closed switch, in which the free ends of the platelets are in contact, to a second state, corresponding to an open switch, in which said contact is broken. A detection module allows, for each sensor, a resistance of the electrical circuit to be measured, the resistance corresponding to the RTDs being connected in parallel when the switch is closed or to one of the RTDs when the switch is open.
    Type: Grant
    Filed: November 30, 2017
    Date of Patent: March 3, 2020
    Assignee: Airbus Operations S.A.S.
    Inventor: Pierre Charon
  • Patent number: 10571318
    Abstract: A simple device for accurately measuring real-time air flows along a wall, and relating to a measuring device including an optical sensor configured to measure an illuminance distribution on a free surface of the optical sensor. A mobile member movably is mounted on the light sensor by partially covering its free surface, the mobile member being adapted to be freely directed by a local air flow pattern, thus, modulating the illuminance distribution on the free surface so as a current illuminance distribution measurement by the optical sensor indicates the current direction of the mobile member representing the current air flow pattern.
    Type: Grant
    Filed: September 14, 2016
    Date of Patent: February 25, 2020
    Assignees: AIRBUS (S.A.S.), Airbus Operations (S.A.S.)
    Inventors: Jean-Luc Vialatte, Philippe Tatry, Gilles Studer, Laurent Malard, Nicolas Benoit
  • Patent number: 10562639
    Abstract: In order to reduce congestion of attachments between an aircraft engine and its attachments, an engine assembly is provided, the primary structure of the device of which includes a structural cover surrounding the engine and connected on a central box, the cover including an outer skin interiorly delimiting a secondary flow. A group of main mounts is provided as a group of secondary mounts laid out at the rear of the group of main mounts, the group of main mounts including a plurality of bolts distributed around the longitudinal axis of the engine and ensuring the attachment of a front end of the cover to the hub of the intermediate case, and a group of secondary mounts including a plurality of secondary mounts distributed around the axis and ensuring attachment of a rear portion of the engine to a rear end of the cover.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: February 18, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Olivier Pautis, Jean-Michel Rogero
  • Patent number: 10546596
    Abstract: A method of measuring state of vigilance of a pilot by a measuring device to measure time between which a sound wave is emitted by a loudspeaker in the piloting station of an aircraft and is received by the microphone of a headset of a pilot and to calculate coordinates of a sphere centered on the loudspeaker and on the perimeter of which the microphone is situated. Calculation of points of intersection of spheres centered on different loudspeakers provides possible microphone positions in the space of the piloting station. These positions are those of the head of the pilot when the headset is used. Via the knowledge of at least one possible position of the head of the pilot in the piloting station, the measuring device can measure the state of vigilance of the pilot and to alert in case of a confirmed lack of vigilance of the pilot.
    Type: Grant
    Filed: February 19, 2019
    Date of Patent: January 28, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Nicolas Clement, Benoît Guaduin
  • Publication number: 20200017191
    Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.
    Type: Application
    Filed: July 10, 2019
    Publication date: January 16, 2020
    Applicant: Airbus Operations S.A.S.
    Inventors: Alain Porte, Francois Pons, Arnaud Bourhis, Julien Sentier
  • Patent number: 10535274
    Abstract: In operating an aircraft, a situation is displayed at each instant representing a spatio-temporal overview of risk zones around the aircraft. Each direction in space around the aircraft is scanned, and a simulated displacement of the aircraft in each direction is analyzed so as to identify potential zones of interference with the aircraft's path. Anticipated movement of risk zones over a planned time duration of a flight is determined. Such anticipated movement is correlated with an anticipation position of the aircraft over the planned time duration. Accordingly, risk zones initially appearing as a potential hazard may be determined to be safe by the time the aircraft reaches them, and vice versa. Such information is presented to pilots at an outset of the flight and continuously updated throughout the flight, enabling accurate and safe evaluation and strategy decisions.
    Type: Grant
    Filed: August 3, 2017
    Date of Patent: January 14, 2020
    Assignee: Airbus Operations S.A.S.
    Inventor: Jean-Claude Mere
  • Publication number: 20200010165
    Abstract: A sensor is fixed on an aircraft structure by a joining system which includes at least one enclosure in which is positioned at least one transducer, at least one passage configured to allow at least one conducting element to pass through the enclosure, at least one flexible connection connecting each transducer present in the enclosure to said enclosure and at least one binder joining together the enclosure and the structure. This joining system makes it possible to limit the spread of the deformations of the structure toward the transducer or transducers and ultimately the risks of malfunction.
    Type: Application
    Filed: June 26, 2019
    Publication date: January 9, 2020
    Applicant: Airbus Operations S.A.S.
    Inventor: Marie-Anne De Smet
  • Patent number: 10526074
    Abstract: A system for the control of the door assemblies of a bay of a landing gear of an aircraft, that is retractile and is able to be deployed, the opening of the bay for the landing gear being able to be closed by a forward door assembly and an aft door assembly, comprises a coupling mechanism of the forward door assembly and the aft door assembly, that is configured such that the aft door assembly is not completely closed, but is ajar, as soon as the forward door assembly is opened during the deployment of the landing gear and the aft door assembly is completely closed at the complete closing of the forward door assembly when the landing gear is retracted.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: January 7, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Christian Cros, Jérôme Phalippou, Christophe Mialhe, Jacques Peres
  • Publication number: 20200002016
    Abstract: A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.
    Type: Application
    Filed: June 13, 2019
    Publication date: January 2, 2020
    Applicant: Airbus Operations S.A.S.
    Inventors: Clément Breton, Julien Sentier, Frédéric Vinches, Alain Porte, Wolfgang Brochard
  • Patent number: 10518897
    Abstract: A method and device for displaying a symbology for assisting the piloting of an aircraft during a landing phase. The display device allows a crew to anticipate or avoid emission of a runway overrun warning, able to be emitted by a piloting assistance unit. The display device includes a display unit to display a symbology, a module for determining characteristics of the runway and an end of runway margin, a module for determining a run distance necessary for the aircraft to attain a run speed, when the piloting assistance unit operates in a first mode, a transmission module configured for transmitting a set of signals making it possible for the display unit to display a symbol representative of the run distance, at least one symbols representative of the characteristics of the runway and a symbol representative of the end of runway margin.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: December 31, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Christine Charbonnier, Rodolphe Bonet, Laetitia Thenault
  • Publication number: 20190389596
    Abstract: A transverse framework for an avionics bay of an aircraft is delimited by a primary structure and a floor, the transverse framework having a mesh structure with square and/or rectangular mesh cells. According to one arrangement, an avionics bay of an aircraft includes two longitudinal rows of avionics racks, parallel to the longitudinal direction and arranged on each side of a clear zone, and a transverse avionics rack supported by the transverse framework situated to the rear of the two longitudinal rows of avionics racks at the rear boundary of the avionics bay. This transverse framework makes it possible to optimize the space occupied by the avionics bay.
    Type: Application
    Filed: June 13, 2019
    Publication date: December 26, 2019
    Applicant: Airbus Operations S.A.S.
    Inventors: Laurent Saint-Marc, Bernard Guering
  • Patent number: 10516472
    Abstract: A device and system for transferring information from an avionics system of an aircraft to an independent computer. The device can be embedded onboard an aircraft for transferring information arising from an avionics system from the aircraft to a computer independent of the avionics system. The device includes at least one radiofrequency receiver configured to receive information which arises from the avionics system and is emitted destined for the ground or another aircraft, at least one transmitter, and a processing unit to command the transmission by the transmitter, to the computer, of at least some of the information received by the radiofrequency receiver.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: December 24, 2019
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Pierre Scacchi, Thomas Stanislawiak, Marc Audibert, Raphaël Renier, Pierre Depape, Martial Pohin
  • Patent number: 10500710
    Abstract: A guiding device includes a rail which extends in a direction, a plurality of runners distributed in the direction, and, for each runner, at least one runner/rail connection connecting each runner and the rail, configured to allow each runner to pivot independently from the other runners relative to the rail, around an axis of pivoting parallel to the direction.
    Type: Grant
    Filed: December 7, 2017
    Date of Patent: December 10, 2019
    Assignee: Airbus Operations S.A.S.
    Inventors: Fabien Albert, Perig Le-Henaff
  • Patent number: 10501207
    Abstract: A system for assisting in guiding of an aircraft maneuvered by an aircraft tractor on the ground, the system including at least one projection device including a laser generating a laser beam fixed to an anchor point of the fuselage of the aircraft. A fixing mechanism is configured to fix the projection device to an anchor point of the fuselage, the laser beam from each laser projector then plotting a light trace on the ground to be used to assist in guiding the aircraft on the ground. A camera can film the light trace on the ground. A remote display device includes a screen, the display device being positioned on the aircraft tractor for the screen to be visible to an operator of the aircraft tractor, each projection device being connected to the display device, the display device being configured to display the image from each projection device camera.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: December 10, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Cyril Carradori, Ludovic Zimmermann, Antoine Rouiller, Patrick Orfila, Philippe Couzinie
  • Publication number: 20190368891
    Abstract: A desensitization device includes an acquisition module for acquiring the current flight parameters of the aircraft, a generation module for generating a first image depicting flight symbology including at least one reference zero pitch line, a generation module for generating a second image depicting topography of terrain overflown by the aircraft, a generation module for generating a third image including at least two portions separated by a separating line, a generation module configured to generate a fourth image by superposing the first image, the second image and the third image in that order, the first image being placed in the foreground, and a transmission module configured to transmit, to a user device, a signal that is representative of the fourth image.
    Type: Application
    Filed: May 16, 2019
    Publication date: December 5, 2019
    Applicant: Airbus Operations S.A.S.
    Inventors: Jerome Gouillou, Aymeric Perrin
  • Patent number: 10489464
    Abstract: Automation of the extraction and the consolidation of maintenance data and relates to a method and a system for automatic integration of data among a plurality of maintenance data, the plurality of maintenance data being diffused through a set of maintenance documentary elements comprising a set of directed links, the system including a processor configured for extracting a subset of pertinent links according to predetermined extraction rules and for integrating into a resultant element pertinent maintenance data sourced from a subset of pertinent maintenance documentary elements associated with the subset of pertinent links.
    Type: Grant
    Filed: October 12, 2015
    Date of Patent: November 26, 2019
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Dang Nguyen Manh, David Marty, Stéphane Sentenac, Maria del Carmen Trigo Romero, Mathieu Dhainaut, Jean-Claude Gallo, Jean-Max Huet
  • Patent number: 10490085
    Abstract: A method and device for identification of a recipient aircraft of an audio communication. The device includes at least one reception unit, for example a VHF radio or an HF radio, for receiving an audio message on board the aircraft, a transcription unit for transcribing the audio message received into a text message, an analysis unit for analyzing the text message in order to extract interpretation data therefrom, a data generation assembly for determining flight data of the aircraft, a processing unit for determining discriminating data from these flight data, a comparison unit for comparing the interpretation data to the discriminating data so as to deduce therefrom whether the audio message received is indeed intended for the aircraft or not, and an indication unit for indicating to at least one crew member of the aircraft whether the aircraft is recipient or not of the audio message received.
    Type: Grant
    Filed: September 18, 2017
    Date of Patent: November 26, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Fabrice Cotdeloup, Francois Courbun
  • Patent number: 10490090
    Abstract: A method and device for adjusting performance variables of an aircraft. The device which is intended for adjusting performance variables, the performance variables being generated by at least one performance module, includes an auxiliary data input unit for entering into a flight management system correction data intended to be used for adjusting at least one associated performance variable, and a correction unit for carrying out a correction, the correction including adjusting the associated performance variable on the basis of the input correction data.
    Type: Grant
    Filed: December 13, 2017
    Date of Patent: November 26, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Esteban Quiroz-Hernandez, Christophe Bouchet, Jean-Pierre Demortier, Sylvain Raynaud, François Cusset, Marc Vie, Alexandre Grattard