公开(公告)号：US11945593B2

公开(公告)日：2024-04-02

申请号：US17783117

申请日：2020-10-05

Applicant: Airbus SAS

Inventor： Daniel Kierbel

IPC: B64D27/24 ,  B64D37/04 ,  B64D37/06 ,  B64D37/30

CPC classification number: B64D27/24 ,  B64D37/04 ,  B64D37/06 ,  B64D37/30 ,  B64D2221/00 ,  H01M2250/20

Abstract: A propulsion system comprising a nacelle with an air channel along a longitudinal direction, an electric motor whose output drives a propeller, and a fuel cell, comprising a core outside the air channel, open channels, each of which has an inlet and an outlet opening in the air channel, and, for each open channel, a fuel chamber, an electrolyte between the open channel and the fuel chamber, a cathode, and an anode, each open channel having an inlet surface area which is less than the surface area of an intermediate area between the inlet and the outlet, the surface area of the outlet being smaller than the surface area of the intermediate area. Such a system makes it possible to have the fuel cell close to the electric motor, thereby reducing the lengths of the electrical conductors between them, and consequently improving the operation of the fuel cell.

公开(公告)号：US20240067020A1

公开(公告)日：2024-02-29

申请号：US18452786

申请日：2023-08-21

Applicant: Airbus SAS

Inventor： Ivan REVEL ,  Didier CHASSAIGNE ,  Frederic FORGET ,  Antoine LOEHRMANN ,  Olivier CREPEL

IPC: B60L53/38 ,  B60L53/12 ,  B60L53/302

CPC classification number: B60L53/38 ,  B60L53/12 ,  B60L53/302 ,  B60L2200/10

Abstract: An electrical-energy transfer device comprising first and second parts able to move one relative to the other between distanced and close-up states, the first part comprising a first housing configured to at least partially house the second part, comprising at least a first lateral surface on which at least a first electrical-energy transfer element is positioned, the second part having a second lateral surface for each first lateral surface of the housing, having an overall shape that complements the shape of the first housing and on which surface there is positioned at least one second electrical-energy transfer element, the first and second electrical-energy transfer elements performing a transfer of electrical energy between one another when the first and second parts are in the close-up state.

公开(公告)号：US20230410668A1

公开(公告)日：2023-12-21

申请号：US18333841

申请日：2023-06-13

Applicant: Airbus SAS

Inventor： Jordan Lee ADAMS ,  Guillaume TA ,  Clément FROT

IPC: G08G5/00 ,  G05D1/10

CPC classification number: G08G5/0047 ,  G08G5/0017 ,  G05D1/106

Abstract: A method for managing a longitudinal position a follower aircraft following a leader aircraft by: obtaining a position and speed of the leader aircraft and a real longitudinal position and speed of the follower aircraft; determining a target longitudinal position of the follower aircraft with respect to the longitudinal position of the leader aircraft; calculating a difference between the target longitudinal position of the follower aircraft and the real longitudinal position of the follower aircraft; comparing the value of the difference with at least one predefined threshold; choosing a control law for controlling the speed of the follower aircraft, from among at least two separate control laws, on the basis of the comparison; and, applying the chosen control law so as to manage the real longitudinal position of the follower aircraft with respect to the position of the leader aircraft.

公开(公告)号：US11840962B2

公开(公告)日：2023-12-12

申请号：US17878331

申请日：2022-08-01

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel Czapla ,  Antoine Abele ,  Benjamin Thubert ,  Alexis Pissavin ,  Abhishek Verma ,  Alistair Forbes ,  Jorge A. Carretero Benignos ,  Benedikt Bammer

IPC: F02C7/224 ,  B64D37/04 ,  B64D37/30 ,  F02C3/22 ,  B64D37/34 ,  F02C7/22 ,  F02C9/40

CPC classification number: F02C7/224 ,  B64D37/04 ,  B64D37/30 ,  B64D37/34 ,  F02C3/22 ,  F02C7/222 ,  F02C9/40 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/606

Abstract: An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.

公开(公告)号：US11840350B2

公开(公告)日：2023-12-12

申请号：US17629477

申请日：2020-07-07

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Nicolas Rapin ,  Didier Poirier ,  Etienne Foch ,  Paul-Emile Roux ,  Emmanuelle Escorihuela ,  Caroline Barnier ,  Guillaume Alix

IPC: B64D31/06 ,  B64D41/00 ,  F02C6/04 ,  F02C9/50 ,  F02C9/00 ,  B64D13/06

CPC classification number: B64D31/06 ,  B64D41/00 ,  F02C6/04 ,  F02C9/00 ,  F02C9/50 ,  B64D2013/0603 ,  F05D2270/101 ,  F05D2270/44

Abstract: A system for controlling idle speed and power draw includes a determination unit configured to determine a current available power value, a determination unit configured to determine a current power consumption value, a determination unit configured to determine a future power requirement variation value, a computation unit configured to calculate a future estimated total power requirement value, a computation unit configured to calculate a future estimated available power value, an optimization unit configured to determine an optimization result by comparing the estimated total power requirement value with a power value associated with an optimization criterion and a controller configured to send an order to adapt an idle speed of the engine, an order to adapt the estimated total power requirement or no order as a function of the optimization result.

公开(公告)号：US20230359225A1

公开(公告)日：2023-11-09

申请号：US18310014

申请日：2023-05-01

Applicant: Airbus SAS

Inventor： Clément FROT ,  Guillaume TA ,  Jordan Lee ADAMS

IPC: G05D1/10

CPC classification number: G05D1/104

Abstract: A system for assisting formation flight, on board a follower aircraft, determines an estimated position of a wake vortex generated by a leader aircraft and inducing an upward airflow. The system determines a first trajectory, intended to be followed by the follower aircraft, as a trajectory for approaching and tracking the wake vortex, while remaining outside a potential discomfort window. The system determines a second trajectory corresponding to a phantom aircraft as if the follower aircraft is permanently in an optimal position relative to the wake vortex. The system assesses future overshoots of the phantom aircraft relative to maneuvering capabilities of the follower aircraft and to passenger comfort rules. The system possibly modifies the first trajectory as a function of the assessed overshoots.

公开(公告)号：US20230305035A1

公开(公告)日：2023-09-28

申请号：US18188688

申请日：2023-03-23

Applicant: Airbus Operations GmbH ,  Airbus SAS ,  Ostbayerische Technische Hochschule Regensburg

Inventor： Alois FRIEDBERGER ,  Bruno STEFES ,  Dominik BERNDT ,  Rupert SCHREINER

IPC: G01P5/12

CPC classification number: G01P5/12

Abstract: A method for determining flow properties of a fluid flowing along a surface by: modulating the current through a heating element of a thermal flow sensor located on the surface with at least one modulation frequency, thereby emitting a thermal wave into the fluid flowing along the surface having a penetration depth inversely proportional to the modulation frequency; measuring an amplitude of a voltage across the heating element at the third harmonic of the at least one modulation frequency, the voltage depending on the thermal conductivity and the volumetric heat capacity of the fluid flowing along the surface; determining a flow velocity at the penetration depth from the attenuation value of the determined amplitude of the voltage; and estimating whether the flow at the penetration depth is laminar or turbulent on the basis of the determined flow velocity. Also, a system and an aircraft with such a system.

公开(公告)号：US20230294836A1

公开(公告)日：2023-09-21

申请号：US18182899

申请日：2023-03-13

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Darren PAGET ,  Vincent LAMONZIE ,  Norberto SIMIONATO NETO

IPC: B64D33/10 ,  B64D27/24

CPC classification number: B64D33/10 ,  B64D27/24

Abstract: A propulsion system for an aircraft comprises a closed cooling circuit which has at least one main segment and at least two secondary segments, in which a heat-transfer fluid circulates. Each secondary segment has: a leak detection device, a shut-off valve, and a non-return valve. The cooling circuit also has electronic circuitry configured to close the shut-off valve of a secondary segment when a leak is detected by the leak detection device of said secondary segment.

公开(公告)号：US20230260412A1

公开(公告)日：2023-08-17

申请号：US18170910

申请日：2023-02-17

Applicant: Airbus SAS ,  Airbus Operations Limited ,  Airbus Operations SAS

Inventor： Marcellin BUISSON ,  Dylan REYNOLDS ,  Jerome GOUILLOU ,  Gabriel LOUPIAC ,  Kiran Kumar CHIPPA

IPC: G08G5/06 ,  G08G5/00

CPC classification number: G08G5/065 ,  G08G5/003

Abstract: Processes and systems for operating an aircraft having a first engine and a second engine, a non-transitory computer readable media comprising computer executable instructions that when executed cause a processor to execute the steps of the present processes. A plurality of taxiways are determined and zones for changing to or from single engine taxing operations are also determined and displayed. Additionally, countdown timers for takeoff or engine shutdown may be displayed.

公开(公告)号：US20230227175A1

公开(公告)日：2023-07-20

申请号：US18156158

申请日：2023-01-18

Applicant: AIRBUS OPERATIONS LIMITED ,  Airbus (SAS)

Inventor： Andrew BILL ,  Colin SMART

IPC: B64D45/00 ,  B64F5/60

CPC classification number: B64D45/00 ,  B64F5/60 ,  B64D2045/0085

Abstract: A system including an aircraft, and a computing system remote from the aircraft. The aircraft includes a sensor, an aircraft component associated with the sensor, a first transmitter, and a first receiver. The computing system includes a processor, a second transmitter, and a second receiver. The aircraft transmits sensor data sensed by the sensor to the computing system. The computing system is configured to process the received sensor data to generate status data indicative of an operational mode of the aircraft component, and to transmit, when the status data is indicative of an altered operational mode of the aircraft component, the status data to the aircraft via the second transmitter. The aircraft is configured to indicate, based at least partially on the status data received by the first receiver, the altered operational mode of the aircraft component.