公开(公告)号：US12065239B2

公开(公告)日：2024-08-20

申请号：US17940073

申请日：2022-09-08

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Andrew Booth ,  Julien Laverne ,  Alistair Forbes

IPC: B64C3/10 ,  B64D37/04

CPC classification number: B64C3/10 ,  B64D37/04

Abstract: An aircraft comprising a fuselage, first and second wings positioned on either side of the fuselage, wherein each wing includes an inner part connected to the fuselage and an outer part continuing the inner part, the end of each inner part connected to the fuselage having a height greater than half the height of the fuselage and extending over a length greater than or equal to half of a distance separating the nose and the tail of the fuselage.

公开(公告)号：US12037133B2

公开(公告)日：2024-07-16

申请号：US18071862

申请日：2022-11-30

Applicant: AIRBUS SAS

Inventor： Thomas Fulcher

IPC: B64D45/02 ,  B64D27/24 ,  B64D27/40 ,  H01B9/02 ,  H02K7/18

CPC classification number: B64D45/02 ,  B64D27/24 ,  B64D27/40 ,  H01B9/02 ,  H02K7/1807 ,  B64D2221/00

Abstract: An aircraft is disclosed include wiring configured to carry electrical power; and an electromagnetic shielding arrangement which provides an enclosure around the wiring and is configured to block electromagnetic emissions from the wiring. The electromagnetic shielding arrangement includes a first shield; a second shield which can move relative to the first shield; and a gap between overlapping portions of the shields. The gap is configured to enable air to flow into or out of the enclosure via the gap.

公开(公告)号：US20240199222A1

公开(公告)日：2024-06-20

申请号：US18541527

申请日：2023-12-15

Applicant: Airbus SAS

Inventor： Timin JACOB ,  Ludovic YBANEZ ,  Matteo TASSISTO ,  Swapnil KHARCHE ,  Ravi Kiran SURAPANENI ,  Gowtham GALLA

IPC: B64D37/32 ,  F17C13/04

CPC classification number: B64D37/32 ,  F17C13/04 ,  F17C2223/0161 ,  F17C2250/043

Abstract: A cryogenic system configured to cool down components and including a housing and a thermal coupling system able to thermally connect a cryogenic fluid tank and the housing, the housing being airtight and being arranged to contain at least one component. The cryogenic system includes: an inert fluid tank, the inert fluid including at least one of the inert gas or nitrogen; a first opening connected to the inert fluid tank; a second opening connected to a relief valve configured to release gas from the housing when the pressure inside the housing exceeds a predefined pressure value; a third opening connected to an exhaust line, and a shut-off valve disposed on the exhaust line. The component is thus thermally and chemically isolated from the outside of the housing without using vacuum.

公开(公告)号：US12014639B2

公开(公告)日：2024-06-18

申请号：US16951896

申请日：2020-11-18

Applicant: Airbus SAS

Inventor： Imad Lebbos ,  Daniel Percy

IPC: B64F5/60 ,  G01C21/20 ,  G05D1/00 ,  G08G5/00

CPC classification number: G08G5/0039 ,  B64F5/60 ,  G01C21/20 ,  G05D1/042 ,  G05D1/104

Abstract: A process for pairing two aircraft together to save fuel. After evaluating whether two aircraft may possibly be paired together in a formation for fuel savings, the process determines new flight plans for both aircraft, allowing the second aircraft to save fuel by flying behind the first aircraft so that the second aircraft utilizes the energy of the wake vortices generated by the first aircraft. Based on the new flight plan, the process determines if there is a net trip fuel savings for the pair.

公开(公告)号：US20240167186A1

公开(公告)日：2024-05-23

申请号：US18307867

申请日：2023-04-27

Applicant: Airbus SAS ,  Airbus Operations GmbH

Inventor： Mariana PAZ MARTINEZ-VIDAMONTE ,  Theodor HACK ,  Malte BURCHARDT ,  Martin BENEKE

IPC: C25D11/10 ,  C09D5/00 ,  C09D163/00 ,  C25D11/08 ,  C25D11/16

CPC classification number: C25D11/10 ,  C09D5/002 ,  C09D163/00 ,  C25D11/08 ,  C25D11/16

Abstract: To improve adhesion of Cr(VI)-free primers and suitable topcoats on aircraft parts, a method for anodizing part surface of the aircraft part that includes aluminum or an aluminum alloy including the steps of cleaning the part and exposing the part to an anodizing electrolyte. During anodizing it is essential that the temperature of the anodizing electrolyte is maintained at a constant temperature chosen from a range from 42° C. to 60° C.

公开(公告)号：US20240116650A1

公开(公告)日：2024-04-11

申请号：US18480080

申请日：2023-10-03

Applicant: Airbus SAS

Inventor： Christian METZNER ,  Uwe BEIER ,  Kristian ZIMMERMANN

IPC: B64D37/30 ,  B64D37/06

CPC classification number: B64D37/30 ,  B64D37/06

Abstract: An aircraft, including a hydrogen consumer and a hydrogen supply device for supplying the hydrogen consumer with hydrogen, the hydrogen supply device having a cryogenic hydrogen tank for storing liquid hydrogen. In order to lower the weight while improving performance of the hydrogen tank during different flight conditions, embodiments of the aircraft further include a suspension arrangement with suspension elements for suspending the hydrogen tank on a structure of the aircraft, wherein the hydrogen tank includes a tank wall made from fiber reinforced composite material, and wherein the suspension arrangement includes a plurality of first tensile loaded dry fiber suspension elements fixed to load introduction areas on the hydrogen tank such that the suspension elements extend essentially tangential to a surface of the hydrogen tank at the associated load introduction area.

公开(公告)号：US11954954B2

公开(公告)日：2024-04-09

申请号：US16661553

申请日：2019-10-23

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Alain Lagarrigue ,  David Cumer ,  Subodh Kumar Keshri

IPC: G07C5/08 ,  B64D45/00 ,  G05B23/02

CPC classification number: G07C5/0816 ,  B64D45/00 ,  G05B23/0283 ,  G07C5/0808 ,  G07C5/085 ,  B64D2045/0065 ,  B64D2045/0085

Abstract: To reduce the bulk of the acquisition systems embedded onboard an aircraft and dedicated to predicting failures, an acquisition system is provided comprising an avionics rack and at least one recording device, in which the avionics rack comprises a front panel provided with at least one test connector configured to be connected to all or some of the data buses of the aircraft, each recording device comprises a housing and an acquisition port, the acquisition port being provided on an outer face of the housing, the acquisition port of each recording device is engaged with a corresponding test connector of the avionics rack, each recording device is configured to acquire at least some signals applied to the acquisition port by the corresponding test connector, and to store the acquired signals.

公开(公告)号：US20240109667A1

公开(公告)日：2024-04-04

申请号：US18476579

申请日：2023-09-28

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Alexis PISSAVIN

IPC: B64D37/30 ,  B64D27/12 ,  F02C7/22

CPC classification number: B64D37/30 ,  B64D27/12 ,  F02C7/22

Abstract: A propulsion assembly for an aircraft, which has a propulsion system with a combustion chamber surrounded by a casing, a supply pipe that conveys dihydrogen to the combustion chamber through the casing via injectors, and a housing fastened to the casing in a sealed manner around the latter, wherein the supply pipe has a downstream part housed inside the housing and wherein the injectors are also housed inside the housing.

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.