Patents Assigned to Airbus Operations S.A.S.
  • Patent number: 10130011
    Abstract: A cabinet designed to accommodate at least one item of electronic equipment and a system for interconnecting such a cabinet with the external networks for blowing and extracting air. The system includes at least one of a blowing inlet and an extracting outlet including a plurality of orifices and at least one hollow structural upright as a part of the blowing circuit or of the extracting circuit.
    Type: Grant
    Filed: September 24, 2014
    Date of Patent: November 13, 2018
    Assignee: Airbus Operations S.A.S.
    Inventors: Bernard Guering, Laurent Saint-Marc
  • Patent number: 10121385
    Abstract: Method and device for estimating lateral speed and lateral position of an aircraft during a phase where the aircraft is traveling on the ground. The device includes a unit for determining an initial lateral position value, corresponding to lateral position with respect to axis of a runway when touching down on landing, a unit for repetitively determining, at least from runway touch down, current ground speed and a current lateral angular deviation, representing angular deviation between the current route and the heading of the runway, a unit for repetitively computing current lateral speed, from the current ground speed and current lateral angular deviation, a unit for computing a current lateral position, from current lateral speed and initial lateral position, and a link for transmitting the current lateral speed and/or the current lateral position to at least one user system.
    Type: Grant
    Filed: November 29, 2016
    Date of Patent: November 6, 2018
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Fabien Guignard, Priteche Venilal
  • Patent number: 10118711
    Abstract: The disclosure herein relates to a method of controlling the thrust of the jets of a multi-jet aircraft, during the aircraft takeoff phase, which successively comprises a first step of controlling the jets to a first thrust level, until the aircraft reaches a first predetermined speed, and a second step of controlling the jets to a second thrust level, less than the first thrust level, when the aircraft exhibits a speed greater than the first predetermined speed, the first predetermined speed being less than the minimum ground control speed of the aircraft when the jets are at the second thrust level.
    Type: Grant
    Filed: November 22, 2016
    Date of Patent: November 6, 2018
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Cédric Consola, Olivier Blusson, Jean-Philippe Sabathier
  • Patent number: 10113224
    Abstract: An adjustment interface inserted between a first part made of nickel or made of nickel alloy or made of cobalt-chromium alloy in relative motion with a second part made of nickel or made of nickel alloy or made of cobalt-chromium alloy. The interface includes a first adjustment layer on one of the two parts and has a composition that makes it possible, with the friction with the other part, to create a glaze-type layer. A second adjustment layer is deposited on the second part for cooperation with the first layer to act as a catalyst for the oxide formed by friction with the first layer. The first glaze layer of the interface improves the sliding of the parts under friction. The catalyst function provided by the second layer makes it possible to stabilize the oxide formed by friction and to thus ensure a lubrication function over an extended high-temperature range.
    Type: Grant
    Filed: October 14, 2016
    Date of Patent: October 30, 2018
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Cédric Poupon
  • Publication number: 20180304994
    Abstract: A flight control computer of an aircraft is likely to operate in a so-called incidence protection mode in which it is configured to compute the deflection orders of an elevator as a function of incidence angle values supplied by a set of incidence probes, so as to keep the incidence angle of the aircraft within a range of acceptable incidence angle values. The flight control computer is configured to, when only one incidence probe is operational: compute a first estimated incidence angle value of the aircraft, by a first estimator and a second estimated incidence angle value of the aircraft, by a second estimator unlike the first estimator; and keep the incidence protection mode activated as long as the incidence angle value supplied by the single operational incidence probe is consistent with at least one out of the first estimated incidence angle value and the second estimated incidence angle value.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 25, 2018
    Applicant: Airbus Operations S.A.S.
    Inventors: Jérôme Gauvain, Lionel Bompart, Daniel Lopez Fernandez
  • Publication number: 20180308369
    Abstract: A method for transmitting flight parameters from a leading aircraft (L) to at least one intruding aircraft (I), wherein, the transmission is effected by a collision avoidance system of TCAS type. The transponder of the leading aircraft (L) is configured to measure the spectrum of an interrogation signal received from the intruding aircraft (I) and to compare the power of the spectrum to a threshold power. If the power of the interrogation signal is greater than or equal to the threshold power, then the intruding aircraft (I) is eligible to receive flight parameters from the leading aircraft to be able to compute the position of the centres or the force of circulation of wake vortexes (14L, 15L) generated by the leading aircraft (L). The exchange of flight parameters from the leading aircraft only to eligible intruding aircraft makes it possible to not exceed the maximum automated communication bandwidth capacity.
    Type: Application
    Filed: April 19, 2018
    Publication date: October 25, 2018
    Applicant: Airbus Operations S.A.S.
    Inventor: Jean-luc Robin
  • Patent number: 10108823
    Abstract: The disclosure relates to a system embedded in an airplane comprising an electronic device intended to be inserted into a frame, a frame that can accommodate the electronic device, in which system the electronic device includes a radiofrequency tag reader, a radiofrequency tag, having a configuration information item, is fixed to the frame such that the radiofrequency tag reader can read the radiofrequency tag once the electronic device is inserted into the frame and the electronic device is adapted to, in a phase of configuration of the electronic device: read the configuration information item via the radiofrequency tag reader and determine a configuration of the electronic device as a function of the configuration information item read.
    Type: Grant
    Filed: October 23, 2017
    Date of Patent: October 23, 2018
    Assignee: AIRBUS OPERATIONS S.A.S.
    Inventors: Stéphane Gauthier, Juan Lopez, Emilie Claudel
  • Patent number: 10105938
    Abstract: The disclosure proposes a method for producing a panel having an outer skin and stiffeners that have a connecting portion, and at least one projecting portion, the method comprising a step of draping layers of fibers over at least one insert such that each layer of fibers has a connecting portion and a portion that projects downwardly from the connecting portion, a step of draping a layer of fibers that forms the outer skin, and a step of bonding the layers of fibers together. The disclosure also provides a device for implementing the method.
    Type: Grant
    Filed: December 1, 2014
    Date of Patent: October 23, 2018
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Dominique Guittard, Mathieu Lannuzel, Philippe Blot, Gilles Bezard
  • Patent number: 10101144
    Abstract: A method for detecting a spacing defect between two adjacent strands of a layer of a fiber fabric includes positioning of the fiber fabric on a metal plate, the fiber fabric covered by an air-tight casing, removing air from between the metal plate and the casing, displacing an inductive sensor relative to the fiber fabric and identifying a defect based on a signal generated by the inductive sensor.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: October 16, 2018
    Assignee: Airbus Operations S.A.S.
    Inventors: Denis De Mattia, Christian Vivier
  • Patent number: 10095971
    Abstract: An onboard system for detecting a temperature of an element includes a radio-tag, the radio-tag being fixed onto the element and having an antenna, the antenna having a load, and a radio-tag reader. The radio-tag reader is designed to emit an interrogation signal and to receive in return a response signal coming from the radio-tag. The load includes a thermistor and the radio-tag reader is adapted for determining a gain and/or a phase-shift between the interrogation signal and the response signal and for deducing a temperature of the element therefrom.
    Type: Grant
    Filed: November 29, 2017
    Date of Patent: October 9, 2018
    Assignee: Airbus Operations S.A.S.
    Inventor: Pierre Charon
  • Publication number: 20180281982
    Abstract: A method and a device for controlling an aircraft propulsion assembly which mitigates the drawbacks of the application of a protection mode in which the maximum thrust is reduced (a degraded operating mode), in particular when an emergency situation occurs or the switch to protection mode is due to an incorrect analysis of the operating parameters of the propulsion assembly. The method includes a sequence of positions of the thrust control consisting in bringing the thrust control to idle then to setting it into the position corresponding to the desired thrust or a setting of the control to the maximum thrust position. Other simple sequences may include, the transition through the idling position with a transition to maximum thrust position, or through a succession of positions relative to the current position of the thrust control at the moment of the switch to degraded mode.
    Type: Application
    Filed: March 28, 2018
    Publication date: October 4, 2018
    Applicant: Airbus Operations S.A.S.
    Inventors: Patrick Zaccaria, Sébastien Tranchard
  • Publication number: 20180281974
    Abstract: A retractable chair for an aircraft cabin which is connected in use to a wall of the cabin, and includes an articulated frame having a back and a seat; a support which is connected to the frame, and fitted such as to be mobile on the wall around an axis of rotation; and at least one covering stretched on the frame. The fact of pivoting the support relative to the wall makes it possible to be able to incline the back, which contributes towards improving the comfort of the chair.
    Type: Application
    Filed: March 28, 2018
    Publication date: October 4, 2018
    Applicants: Airbus Interiors Services, Airbus Operations S.A.S., AIRBUS SAS
    Inventors: Sylvain Mariat, Laid Adda, Béranger Chantal, Nicolas Ferrere, Nicolas Rios, Christophe Arnold
  • Patent number: 10088055
    Abstract: An electric generator for an aircraft includes a sealed casing, a rotating shaft, and a ventilation device, which has at least one orifice configured to place a chamber positioned inside the rotating shaft in communication with the exterior of the sealed casing. For at least one orifice, an inertia sealing system is configured to occupy an open state when the speed of rotation of the rotating shaft is below a given threshold, in which state the sealing system is spaced from the orifice, and a closed state when the speed of rotation of the rotating shaft is above the given threshold, in which state the sealing system seals the orifice.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: October 2, 2018
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventor: David Kaslin
  • Patent number: 10087664
    Abstract: An operating device for operating at least one door of an aircraft comprises a chassis that is fixed and secured to a fuselage of the aircraft, a control handle that is rotationally and translationally movable with respect to the chassis, a mechanism for converting a rotational movement of the control handle into an opening movement of the door. The translational movement allows the control handle to be in an in position in which it is aligned with the exterior surface of the fuselage and an out position in which it projects beyond the exterior surface of the fuselage. The control handle includes a cylindrical body and a head connected to one end of the body. The head of the control handle includes a fixed part rigidly connected to the body of the control handle and extending perpendicular thereto, and a movable part rotatably connected to the body and having a folded-down position against the fixed part and a deployed position in which the control handle has a T shape.
    Type: Grant
    Filed: February 2, 2016
    Date of Patent: October 2, 2018
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventor: Vincent Auriac
  • Publication number: 20180275101
    Abstract: An ultrasound probe for inspecting a bore opening onto a peripheral surface, includes a coupling support which has: a through-orifice to allow the ultrasound probe to pass through, a contact face, which has an external diameter greater than the diameter of the bore to be inspected and is configured to be pressed against the peripheral surface of the bore in order to close the bore.
    Type: Application
    Filed: March 16, 2018
    Publication date: September 27, 2018
    Applicants: Airbus Operations S.A.S., AIRBUS SAS
    Inventors: Alain Tissenier, Aurelien Rautureau
  • Publication number: 20180275103
    Abstract: An ultrasound probe for inspecting a bore opening onto a peripheral surface includes an offcentring device which includes at least two strips which are elastically deformable, connected to the ultrasound probe and configured to keep the emission head of the ultrasound probe pressed firmly against the wall of the bore that is to be inspected.
    Type: Application
    Filed: March 16, 2018
    Publication date: September 27, 2018
    Applicants: Airbus Operations S.A.S., AIRBUS SAS
    Inventors: Alain Tissenier, Aurelien Rautureau
  • Publication number: 20180275655
    Abstract: The invention relates to a flight management assembly (1) comprising two guidance chains (2A, 2B), each one provided with a flight management system (3A, 3B), each of said flight management systems (3A, 3B) carrying out at least one calculation of guidance instructions for the aircraft, the flight management assembly (1) also comprising at least one monitoring unit (4A, 4B) designed to monitor the guidance instructions calculated by the two flight management systems (3A, 3B) in such a way as to be able to detect and identify a defective flight management system, the monitoring unit (4A, 4B) comprising a monitoring device (5) which verifies particularly whether the following three conditions are met: a first derivative of extrapolated cross tracks is positive; a second derivative of extrapolated cross tracks is positive; and extrapolated positions of the aircraft are on the same side of an active segment of the flight plan followed by the aircraft as the current position of the aircraft.
    Type: Application
    Filed: November 24, 2016
    Publication date: September 27, 2018
    Applicant: Airbus Operations S.A.S.
    Inventors: Sylvain Raynaud, Jean-Claude Mere, Simon Sellem
  • Patent number: 10082799
    Abstract: A method and device for assisting initiation of a flare maneuver of an aircraft during a landing. The device includes an acquisition unit for acquiring current values of flight parameters of the aircraft, including the current height of the aircraft with respect to the ground, a computation unit for computing a first reference height and a second reference height, corresponding to a height starting from which the aircraft attains a current start of flare height while maintaining its current descent conditions over a predetermined first duration and over a predetermined second duration respectively, and an acoustic emission unit for emitting at least two sound signals in the cockpit of the aircraft, namely a first sound signal when the current height of the aircraft attains the first reference height during the descent and a second sound signal when the current height of the aircraft attains the second reference height during descent.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: September 25, 2018
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Jerôme Bazile, Patrice Rouquette, Matthias Eberle, Philippe Perrin
  • Patent number: 10081433
    Abstract: A front engine attachment, intended to fix an engine to a structure of an aircraft, includes a first attachment including a base intended to be fixed to the structure, a first fixture articulated on the base, two first connecting rods, each being articulated by a first end to the engine and by a second end to the fixture, and a first cylindrical nose mounted on the base. The front engine attachment includes a second attachment including a cradle including an orifice into which the cylindrical nose is fitted, and a second cylindrical nose being threaded into a piercing of the engine, and two second connecting rods, each being intended to be articulated by a first end to the engine, and by a second end to the cradle.
    Type: Grant
    Filed: October 29, 2015
    Date of Patent: September 25, 2018
    Assignee: Airbus Operations S.A.S.
    Inventor: Jacques Hervé Marche
  • Patent number: 10081346
    Abstract: A braking control system for an aircraft having braking wheels, the braking control system being configured to receive input of signals from sensors representative of a plurality of measured aircraft parameters, and to output a plurality of brake commands to brakes associated with the braking wheels, wherein the braking control system includes a health monitoring system for determining the operability and/or reliability of the sensor signals and/or of the braking wheels, and a task manager for automatically self-reconfiguring the braking control system so as to change the manner in which the braking control system utilises the input signals in the event that the health monitoring system judges a failure of one or more of the braking wheels or sensor signals. Also a method for operating an aircraft having a plurality of braking wheels.
    Type: Grant
    Filed: July 8, 2016
    Date of Patent: September 25, 2018
    Assignees: Airbus Operations Limited, Airbus Operations (S.A.S.)
    Inventors: Louis-Emmanuel Romana, Miguel Angel Gama, Andrea Damiani