公开(公告)号：US20220358849A1

公开(公告)日：2022-11-10

申请号：US17732019

申请日：2022-04-28

Applicant: AIRBUS OPERATIONS LIMITED ,  Airbus SAS

Inventor： George HOWELL ,  Andrew HEBBORN ,  James BULLEN ,  Andrea LARUELO-FERNANDEZ

IPC: G08G5/06 ,  G08G5/00 ,  G08G5/02 ,  B64D45/04

Abstract: An aircraft landing event system is disclosed including a processor, the processor being configured to receive aircraft braking performance information from a plurality of aircraft that have performed a landing event on a particular runway. The processor is configured to determine an aircraft braking performance indicator on the basis of the aircraft braking performance information of the plurality of aircraft, and communicate the aircraft braking performance indicator to an aircraft landing system of an approaching aircraft that is about to perform a landing event on the particular runway.

公开(公告)号：US11465774B2

公开(公告)日：2022-10-11

申请号：US16377834

申请日：2019-04-08

Applicant: Airbus Operations SAS ,  Airbus SAS

Inventor： Christian Gulli ,  Patrick Roussel ,  Patrick Hubert

IPC: B64F1/10 ,  B60D1/18 ,  B64F1/22

Abstract: To avoid the intervention of an operator on a direction control device with which an aircraft towing system is equipped, this system comprises a first towing sling comprising a front end connected to a towing vehicle, and a rear end connected to a first main landing gear, a second towing sling comprising a front end connected to the vehicle, and a rear end connected to a second main landing gear. The direction control device is connected to a front landing gear, and arranged between the first and second slings. The direction control device comprising a lateral direction control member having a first lateral end mounted on the first sling, and a second lateral end mounted on the second sling.

公开(公告)号：US11462763B2

公开(公告)日：2022-10-04

申请号：US17026679

申请日：2020-09-21

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations GmbH

Inventor： Didier Poirier ,  Guido Klewer ,  Anthony Roux ,  Olivier Raspati ,  Matthieu Thomas ,  Olivier Verseux ,  Manuel Silvestre Salas

IPC: H01M8/248 ,  H01M8/04089 ,  H01M8/249

Abstract: A system of fuel cells for an aircraft including a plurality of fuel cells, a hydrogen circuit, a cooling circuit and a first air circuit configured to supply oxygen to a first subset of fuel cells having at least two cells. The first air circuit includes an air flow restrictor at each fuel cell inlet of the first subset and configured to distribute the air between the fuel cells of the first subset, and an outlet valve connected to the outlet of the fuel cells of the first subset, the opening of the outlet valve being controlled by a computer as a function of an electrical power that is to be produced by the fuel cells of the first subset. The use of the same air circuit to supply oxygen to several fuel circuits makes it possible to limit the bulk of the fuel cells system.

公开(公告)号：US20220306306A1

公开(公告)日：2022-09-29

申请号：US17701818

申请日：2022-03-23

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Christophe LABARTHE ,  Franck ALVAREZ ,  Fabien LATOURELLE ,  Olivier VERSEUX ,  Pascal POME ,  Jean Francois ALLIAS ,  Olivier CIET ,  Olivier RASPATI ,  Anthony ROUX ,  Benedikt BAMMER

IPC: B64D27/24 ,  B60L50/70 ,  B64D29/00 ,  B64D33/08 ,  B64C11/00 ,  B60L58/33 ,  F02K5/00

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

公开(公告)号：US11420761B2

公开(公告)日：2022-08-23

申请号：US16898960

申请日：2020-06-11

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations GmbH

Inventor： Matthieu Thomas ,  Anthony Roux ,  Didier Poirier ,  Olivier Verseux ,  André Anger ,  Benedikt Bammer ,  Guido Klewer ,  Guillaume Gallant ,  Florian Vogel ,  Christian Wehle

IPC: B64D35/02 ,  B60L50/71 ,  B64C5/06 ,  B64D27/24 ,  B64D29/02 ,  B64D31/02 ,  B60L58/30 ,  B64C3/32 ,  B64D33/10 ,  B64D37/08 ,  B64D41/00

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

公开(公告)号：USD957306S1

公开(公告)日：2022-07-12

申请号：US29647955

申请日：2018-05-17

Applicant: Airbus SAS

Designer： Jason Zaneboni

公开(公告)号：US20220177146A1

公开(公告)日：2022-06-09

申请号：US17535047

申请日：2021-11-24

Applicant: Airbus SAS

Inventor： Richard FORSTER

IPC: B64D27/24 ,  F02G1/043 ,  B64D33/08

Abstract: An electric propulsion system of an aircraft includes an electrical generator and a cooling device of the electrical generator. It further includes at least one thermoacoustic engine and a heat transfer circuit configured to transport heat dissipated by the electrical generator to the thermoacoustic engine. The cooling device of the electrical generator is at least partially powered by energy from the thermoacoustic engine.

公开(公告)号：US20220140900A1

公开(公告)日：2022-05-05

申请号：US17459696

申请日：2021-08-27

Applicant: AIRBUS SAS

Inventor： Crisanto QUINTANA SANCHEZ ,  Gavin ERRY ,  Yoann THEUX

IPC: H04B10/11 ,  H04B10/70 ,  H04B10/532

Abstract: A free space optical communications transmitter terminal including an optical source arranged to provide a first beam of light encoding information to be communicated; an optical source arranged to provide photons encoding bits of a key of a Quantum Key Distribution protocol; and an optics arrangement. The first beam and the photons are linearly polarised. The optics arrangement is configured to combine the first beam and the photons into a single, second, beam to be transmitted to a receiver terminal; and transform the linear polarisation of the first beam into one of left and right circular polarisation and transform the linear polarisation of the photons into the other of left and right circular polarisation. A receiver terminal receives the second beam, transforms the circular polarisations into orthogonal linear polarisations, and filters out the linear polarisation of the first beam to allow the photons to pass to a single photon detector.

公开(公告)号：US11322763B2

公开(公告)日：2022-05-03

申请号：US17026519

申请日：2020-09-21

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations GmbH

Inventor： Didier Poirier ,  Guido Klewer ,  Anthony Roux ,  Olivier Raspati ,  Matthieu Thomas ,  Olivier Verseux ,  Manuel Silvestre Salas

IPC: H01M8/04746 ,  H01M8/04029 ,  H01M8/0438 ,  H01M8/04007 ,  H01M8/0432 ,  H01M8/04701

Abstract: A system of fuel cells for an aircraft includes a plurality of fuel cells, a hydrogen circuit, an air circuit, and a first cooling circuit configured to cool a first subset of cells including at least two cells. The first cooling circuit includes a computer-controlled device for mixing a first liquid coolant at a first temperature with a second liquid coolant at a second temperature lower than the first temperature to obtain a liquid coolant having a target temperature, a liquid coolant restrictor configured to distribute the liquid coolant between the cells of the first subset, and an outlet valve, the opening of which is controlled by the computer as a function of the cooling needs of the cells of the first subset. The use of a cooling circuit to cool several fuel circuits makes it possible to limit the bulk of the fuel cells system.

公开(公告)号：US20220100168A1

公开(公告)日：2022-03-31

申请号：US17485887

申请日：2021-09-27

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Emeric NOIROT-NERIN ,  Ivan HAMM ,  Gérard POULACHON ,  Frédéric ROSSI

IPC: G05B19/4065 ,  G06N20/00

Abstract: This control system takes into account the thermomechanical aspects of materials to quickly and easily determine optimal cutting conditions and to automatically control machining to preserve the integrity of the workpiece. This system includes an acquisition module configured to acquire values of a set of input parameters relating to cutting conditions and material properties of the piece, and a microprocessor configured for determining at least one operating cutting parameter representative of a cutting signal from the machining apparatus using a set of output parameters of an integrity model previously constructed during a learning phase. The integrity model connects the set of input parameters to the set of output parameters comprising specific cutting coefficients representative of the material integrity of the piece, and establishes at least one fatigue threshold of the at least one cutting operating parameter. The fatigue threshold allows control of the progress of cutting operations.