公开(公告)号：US20230147038A1

公开(公告)日：2023-05-11

申请号：US17982567

申请日：2022-11-08

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

Inventor： Thomas JOSSET ,  Didier POIRIER ,  Holger BAMMANN ,  Thomas SCHERER

IPC: B64D41/00 ,  B64D45/00 ,  B64D13/06 ,  B64D27/24 ,  B64D33/08 ,  B60L58/33 ,  H01M8/04111 ,  H01M8/04746 ,  H01M8/04029 ,  H01M8/04007 ,  H01M8/04664

CPC classification number: B64D41/00 ,  B64D45/00 ,  B64D13/06 ,  B64D27/24 ,  B64D33/08 ,  B60L58/33 ,  H01M8/04111 ,  H01M8/04753 ,  H01M8/04776 ,  H01M8/04029 ,  H01M8/04074 ,  H01M8/04664 ,  B64D2041/005 ,  B64D2013/0618 ,  B64D2013/0611 ,  B64D2045/009 ,  B60L2200/10 ,  H01M2250/20

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

公开(公告)号：US20230139421A1

公开(公告)日：2023-05-04

申请号：US17973644

申请日：2022-10-26

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Philippe PEDOUSSAUT ,  Najoua ERROUI

IPC: F16L59/18 ,  F16L51/03

Abstract: A connection assembly between two portions of a supply line for a cryogenic fluid, the assembly including a male nozzle arranged to be at least partially inserted into a female nozzle together forming a tight mechanical link, over a distance of a few centimeters, a thermal insulation chamber for each of the two line portions and an additional thermal insulation chamber to thermally insulate the connection zone of the two line portions, and an expansion chamber for the cryogenic fluid that is configured to be linked to a cryogenic fluid sensor, arranged about the connection zone of the two line portions. This enables two cryogenic fluid line portions to be connected without requiring one portion to be inserted into the other portion over a significant length, thereby enhancing mechanical flexibility and obviating the need for significant free space about the connection assembly to assemble and disassemble the assembly.

公开(公告)号：US11619645B2

公开(公告)日：2023-04-04

申请号：US16400417

申请日：2019-05-01

Applicant: Airbus SAS

Inventor： Julien Charles ,  Guillaume Ferrer

IPC: B60R19/02 ,  G01P1/07 ,  B60R19/03 ,  G01P1/12

Abstract: A bumper for a vehicle, comprising at least one part made of resilient material, having a curved front portion forming an inner cavity. The front portion has apertures enabling the cavity to be put into communication with the exterior of the resilient part. At least one marking fluid cell is provided inside the cavity. A fastener is provided to fasten the one part to the vehicle.

公开(公告)号：US11618546B2

公开(公告)日：2023-04-04

申请号：US16869074

申请日：2020-05-07

Applicant: Airbus SAS ,  Airbus Operations GmbH

Inventor： Andrew Booth ,  Eckart Frankenberger

IPC: G05B19/402 ,  B64C1/26 ,  B64F5/10

Abstract: A process of joining a wing to an aircraft fuselage comprising the steps of: mapping the wing root of the wing, mapping the center-wing-box (CWB) of the aircraft fuselage, determining the position to provide the hole pattern on the CWB, providing the holes on the CWB, and attaching the wing root to the CWB. Primary and secondary templates with corresponding hole patterns may be used in combination with targets and laser trackers to implement the process. The hole pattern of the wing root can therefore be duplicated on the CWB at a position such that when the wings are joined to the fuselage, the aircraft will have optimum flight performance and dynamic symmetry. A predictive fit is thus provided, based on virtual representation and analysis, and advantageously permits the hole pattern to be provided without requiring the CWB and wing root to be brought together.

公开(公告)号：US20230086495A1

公开(公告)日：2023-03-23

申请号：US17940095

申请日：2022-09-08

Applicant: Airbus SAS

Inventor： Benoit SALGUES

IPC: G01C21/20

Abstract: A method for determining a characteristic associated with a portion of a path of an aircraft includes the following steps, implemented by a processing unit of a computer: acquiring timestamped information relating to points of the path of the aircraft; selecting an interval of successive points of the path, corresponding to the portion of the path; selecting a first predetermined number of subsets of points belonging to the interval of points; determining a value of the characteristic for each subset of points; and determining a value of the characteristic for the interval of points, based on the values of the characteristic that are determined for each subset of points.

公开(公告)号：US11579050B2

公开(公告)日：2023-02-14

申请号：US17190623

申请日：2021-03-03

Applicant: AIRBUS SAS

Inventor： Mathias Farouz-Fouquet

IPC: G01N1/22 ,  B64D47/00 ,  G01N15/02

Abstract: The system, configured for being on board an aircraft, includes a probe for collecting samples of contrail, a chamber for collecting the samples, a collecting conduit for conducting the samples from the collecting probe the collecting chamber and at least one device for measuring at least one parameter characterizing the samples in the collecting conduit while they are conducted from the collecting probe to the collecting chamber. By virtue of the system, it is not necessary to use a second aircraft that follows the aircraft for collecting samples of contrail.

公开(公告)号：US20230043843A1

公开(公告)日：2023-02-09

申请号：US17878346

申请日：2022-08-01

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Alexis PISSAVIN ,  Lionel CZAPLA ,  Alistair FORBES

IPC: B64D37/30 ,  B64D37/32 ,  B64D37/04

Abstract: An aircraft including at least one hydrogen engine, at least one hydrogen supply device including at least one hydrogen tank and at least one item of equipment through which the hydrogen flows and which is positioned between the hydrogen tank and the hydrogen engine. The aircraft includes at least one sealed container sealed from the outside air, in which sealed container the equipment of the hydrogen supply device is positioned. This solution allows a safe hydrogen installation to be obtained using existing equipment.

公开(公告)号：US11522610B2

公开(公告)日：2022-12-06

申请号：US17459982

申请日：2021-08-27

Applicant: AIRBUS SAS

Inventor： Crisanto Quintana Sanchez ,  Gavin Erry ,  Yoann Thueux

IPC: H04B10/118 ,  H04B10/60

Abstract: A free space optical receiver including a multi-mode transmission medium configured to receive a light beam comprising a plurality of modes, the light beam having been propagated through a free space path. The free space optical receiver also includes a mode separating means configured to separate the plurality of modes for transmission through a corresponding first plurality of transmission media as a corresponding plurality of single-mode light beams, and a combining means configured to combine two or more of the plurality of single-mode beams into a combined beam for transmission through a further transmission medium.

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.