公开(公告)号：US20140091188A1

公开(公告)日：2014-04-03

申请号：US14039917

申请日：2013-09-27

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Pierre-Louis Engelvin ,  Patrice Lafont

IPC: F16M13/02

CPC classification number: F16M13/022 ,  G01R31/008 ,  H05K7/1412 ,  H05K7/1454

Abstract: Connection system for connecting an electronic device, in particular for an aircraft, to a test unit. The connection system includes a fixed portion, which is fixable to said test unit, and a movable plate which is capable of receiving the electronic device to be tested and is displaceable linearly with respect to said fixed portion between two positions which correspond respectively to a connection position and a disconnection position of the electronic device, by manually actuated displacement.

Abstract translation: 用于将电子装置，特别是飞机连接到测试装置的连接系统。 连接系统包括可固定到所述测试单元的固定部分，以及能够接收待测试的电子设备的可移动板，并且可相对于所述固定部分线性移动，该两个位置分别对应于连接 位置和电子设备的断开位置。

公开(公告)号：US20130307324A1

公开(公告)日：2013-11-21

申请号：US13864462

申请日：2013-04-17

Applicant: Airbus Operations GmbH ,  Airbus Operations S.A.S.

Inventor： Martin Johannsen ,  Torben Schroeter ,  Lucien Prisse ,  Jerome Mavier ,  Martina Hinze

IPC: H02J1/00

CPC classification number: H02J1/00 ,  H02J4/00 ,  H02J2001/008 ,  Y10T307/25

Abstract: An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network.

Abstract translation: 一种能量供应网络，特别是对于包括第一耦合装置的飞机或航天器，所述第一耦合装置被配置为将所述能量供应网络耦合到外部能量源，第一高压直流电，HVDC段，所述第一HVDC 所述第二连接部分耦合到所述第一耦合装置和第二HVDC段，所述第二HVDC段耦合到所述第一耦合装置。 还提供了一种相应的方法以及包含这种能量供应网络的飞机或航天器。

公开(公告)号：US20130240682A1

公开(公告)日：2013-09-19

申请号：US13793757

申请日：2013-03-11

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Hervé MARCHE ,  Jean GELIOT

IPC: F16L3/10

CPC classification number: F16L3/1075 ,  F16L3/237 ,  F16L55/035 ,  H02G3/32

Abstract: A device for attaching an electrical harness on a structure of an aircraft comprising a support connected to the structure, the harness following a path direction, characterized in that it comprises a body with at least two jaws, at least one of the jaws being movable along a reference plane perpendicular to the path direction between a first open position in which they enable the insertion of at least one harness and a second closed position in which they keep the inserted harness or harnesses in position, and on the other hand, a retainer strip in the form of a blade whose ends are connected to the support allowing for the jaws to be maintained in closed position and the body to be flattened against the support.

Abstract translation: 一种用于将电气线束附接到飞行器的结构上的装置，包括连接到结构的支撑件，沿着路径方向的线束，其特征在于，其包括具有至少两个钳口的主体，所述钳口中的至少一个可沿着 垂直于第一打开位置之间的路径方向的参考平面，在第一打开位置中，使得能够插入至少一个线束和第二闭合位置，在第二闭合位置中，它们将插入的线束或线束保持在适当位置，另一方面，保持器条 其形式为刀片，其刀片的端部连接到支撑件，允许钳口保持在关闭位置，并且使身体平坦地抵靠支撑件。

公开(公告)号：US12214896B2

公开(公告)日：2025-02-04

申请号：US18352511

申请日：2023-07-14

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Matthieu Bradier ,  Mohamed Khaled Kahalerras

IPC: B64D41/00 ,  H02J3/46

Abstract: An electrical supply system (10) with first and second electrical sourced (S1, S2), coupled together to electrically supply electrical loads (Z1, Z2, Z3 . . . Zn) of an aircraft. The first electrical source (S1) is mechanically coupled to a primary energy source (12), to which at least one other energy consumer (16) is coupled. A controller (30) controls the first and second electrical sources (S1, S2) so that the power drawn by the first electrical source from the primary energy source (12) corresponds to a difference between an instantaneous nominal power capable of being delivered by the primary energy source and an instantaneous power drawn by the energy consumer (16), and an electrical power delivered by the second electrical source is a sum of an electrical power delivered by the first and second electrical sources which corresponds to an instantaneous electrical consumption of the electrical loads.

公开(公告)号：US20250011009A1

公开(公告)日：2025-01-09

申请号：US18761677

申请日：2024-07-02

Applicant: Airbus Operations (S.A.S.)

Inventor： Christophe VLACICH ,  Stephan ROUX ,  Thomas MASSONNEAU ,  Driss EL MAAMAR

IPC: B64F5/60 ,  G06N3/08 ,  G07C5/08

Abstract: A method for detecting and localizing a failure of an input sensor of a flight control computer of an aircraft including comparing a first piece of information representative of a probability of occurrence of the failure, delivered by a neural network, with a second piece of information representative of a probability of occurrence of the failure, delivered by a classifier trained to carry out a detection and a localization of the failure. It is thus possible to optimize a failure diagnosis and a localization of a failure of an input sensor used in the determination of flight controls.

公开(公告)号：US20250005783A1

公开(公告)日：2025-01-02

申请号：US18753941

申请日：2024-06-25

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Louise FAURE ,  Thierry SAMMOUR SAWAYA

IPC: G06T7/70 ,  G06T7/10 ,  G06V10/26 ,  G06V10/75 ,  G06V10/82 ,  G06V20/17 ,  G06V20/56 ,  G08G5/02

Abstract: A method and system for detecting a ground marking element of a landing runway by computer vision and through signal processing techniques. A detection system (S) including an image collection unit (10), a cutting unit (11) for cutting the image (I) into strips (ST1), a determination unit (12) to determine at least one mean intensity curve (C) for at least one strip (ST1), a recognition unit (13) for recognizing in the mean intensity curve (C) at least one ground marking element (100) of the landing runway (T), a detection unit (2) for detecting a position of at least one ground marking element of the landing runway (T) in the images (I).

公开(公告)号：US20240404416A1

公开(公告)日：2024-12-05

申请号：US18679229

申请日：2024-05-30

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Juan RIVERO SESMA

IPC: G08G5/02 ,  G06F18/2413 ,  G06T7/70 ,  G06V20/17

Abstract: A method for assisting with landing an aircraft is disclosed and configured to determine a number of probable theoretical positions (POS1, POS2, POS3) of the aircraft equal to the facing plurality of runways of a destination airport facility to reproject the runways into an image (F) obtained by a camera of the aircraft by means of a theoretical camera model (e.g. pinhole camera model), each reprojection being with reference to one of the determined theoretical positions (POS1, POS2, POS3); and to establish, for each of the reprojections, a consistency score making it possible to then deliver an estimated position (POSA) of the aircraft.

公开(公告)号：US20240403506A1

公开(公告)日：2024-12-05

申请号：US18673471

申请日：2024-05-24

Applicant: Airbus Operations (S.A.S.)

Inventor： Jean-Marc DATAS

IPC: G06F30/15 ,  G06F17/16 ,  G06F30/20

Abstract: A simulation of efforts applied to positioners to support the fuselage and the airfoil of an aircraft during operations of assembly is performed. The efforts are defined in a digital model of a load plan of the aircraft in assembly phase. The simulation is performed using the load plan digital model of the aircraft in assembly phase and a digital model of each positioner in the form of a set of three equivalent springs defined by three respective eigenvectors associated with three respective eigenvalues, in which the eigenvalues provide rigidity values and the eigenvectors provide directions on which the respective eigenvalues are applied. Thus, the simulation times are reduced.

公开(公告)号：US12110127B2

公开(公告)日：2024-10-08

申请号：US17972033

申请日：2022-10-24

Applicant: Airbus Operations (S.A.S.)

Inventor： Adeline Soulie

IPC: B64D33/08 ,  B64D29/02 ,  B64D33/04 ,  F28F3/08

CPC classification number: B64D33/08 ,  B64D29/02 ,  B64D33/04 ,  F28F3/08

Abstract: An aircraft propulsion assembly having an engine, a nacelle positioned around the engine, an annular duct delimited by the engine and the nacelle for a bypass flow of cold air, at least one bifurcation passing through the annular duct for connecting the engine and the nacelle and having a leading edge and a primary structure of a pylon housed in the bifurcation and configured to connect the engine to an aircraft wing. The propulsion assembly has at least one heat exchange device including a plate heat exchanger, having a hexagonal longitudinal section and positioned in the bifurcation. According to one configuration, the heat exchanger is a countercurrent heat exchanger.

公开(公告)号：US20240239510A1

公开(公告)日：2024-07-18

申请号：US18415000

申请日：2024-01-17

Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS (S.A.S.) ,  AIRBUS OPERATIONS GmbH

Inventor： Francesco GAMBIOLI ,  Kei Philipp BEHRUZI ,  Jörg KLATTE ,  Damien GUILLOTEAU

IPC: B64D37/22 ,  B64D37/06

CPC classification number: B64D37/22 ,  B64D37/06

Abstract: An aircraft fuel storage system is disclosed including a fuel tank comprising a chamber for storing fuel, the chamber comprising a first side, a second side, and a base connecting the first side to the second side; a collector; and a first conduit and a second conduit, each of the first and second conduits fluidically coupling the chamber to the collector so that fuel is freely passable from the chamber to the collector via the respective first and second conduits. The first and second conduits open into the chamber at respective first and second conduit openings, the first conduit opening is nearer to the first side than the second conduit opening is to the first side, and the second conduit includes a second conduit lock portion that is nearer to the first side than the second conduit opening is to the first side. Also disclosed is an aircraft including the aircraft fuel storage system.