公开(公告)号：US20250162564A1

公开(公告)日：2025-05-22

申请号：US18938883

申请日：2024-11-06

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

Inventor： Mohamed Laraki

IPC: B60T17/22

Abstract: A device for monitoring a maximum temperature reached during landing by a brake of landing gear of an aircraft. The monitoring device uses a prediction model to estimate a maximum temperature reached by the brake during landing. An error between the estimated maximum temperature and the measured maximum temperature is determined, and if the error is greater than a first predefined threshold, when the measured maximum temperature is greater than the estimated maximum temperature, or a second predefined threshold, when the measured maximum temperature is less than the estimated maximum temperature, and if a total number of errors is greater than a third predefined threshold, then a warning message is generated for attention of the flight crew and/or ground crew. It is thus possible to anticipate maintenance actions on landing-gear components.

公开(公告)号：US20250136295A1

公开(公告)日：2025-05-01

申请号：US18929865

申请日：2024-10-29

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

Inventor： Martin Beneke ,  Alexandra Luce ,  Romain Ecault ,  Marine Chesneau

IPC: B64F5/60 ,  G07C5/00 ,  G07C5/08

Abstract: A method and system for optimizing the maintenance of an aircraft structure against corrosion includes a step of collecting corrosion incidents on aircrafts, a step of determining zones and corrosion incident rates in each of the zones, a step of determining zones at risk, a step of determining a depth of corrosion, a step of determining a rate of corrosion, a step of determining a proposed inspection frequency for each of the zones at risk based on its rate of corrosion and a predetermined limit depth of each of the zones at risk. A proposed inspection frequency can be obtained that is more accurate and suited to the different parts of the aircraft structure.

公开(公告)号：US20250136265A1

公开(公告)日：2025-05-01

申请号：US18926829

申请日：2024-10-25

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

Inventor： Mayur K V ,  Nishith RAMARAJA ,  Marc Antonio BENTIVOGLIO ,  Cristobal Federico BRITO MAUR ,  Benoît THOMAS ,  Dominique GRISEL ,  Jayaparthan JAGADEESAN ,  Marco LUTZ

IPC: B64C1/14 ,  E05F15/60

Abstract: A method of opening a cargo door of an aircraft, the aircraft including a body with an opening into a cargo bay, and a cargo door which covers the opening when it is in a closed position. A cargo door is outwardly rotated with a first actuator from the closed position to a first open position. Then an actuator rod is installed by coupling a first end of an actuator rod to the body and coupling a second end of the actuator rod to the cargo door in the first open position. Then the cargo door is outwardly rotated with the actuator rod from the first open position to a second open position by increasing a distance between the first and second ends of the actuator rod.

公开(公告)号：US20250136264A1

公开(公告)日：2025-05-01

申请号：US18926793

申请日：2024-10-25

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

Inventor： Mayur K V ,  Nishith RAMARAJA ,  Marc Antonio BENTIVOGLIO ,  Cristobal Federico BRITO MAUR ,  Benoît THOMAS ,  Dominique GRISEL ,  Jayaparthan JAGADEESAN ,  Marco LUTZ

IPC: B64C1/14

Abstract: An actuation system for a cargo door of an aircraft. The cargo door covers an opening into a cargo bay when it is in a closed position. The actuation system includes a first actuator configured to outwardly rotate the cargo door from the closed position to a first open position, and a second actuator configured to outwardly rotate the cargo door from the first open position to a second open position.

公开(公告)号：US12252273B2

公开(公告)日：2025-03-18

申请号：US18125656

申请日：2023-03-23

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

Inventor： Vincent Nicolas ,  Jamie McGirr

IPC: B64F5/60 ,  B60T8/17 ,  B60T8/172 ,  B64C25/36 ,  B64C25/42 ,  B64D45/00 ,  B64F5/40

Abstract: A method of monitoring friction associated with a plurality of aircraft wheels of an aircraft, the method including, for each of the plurality of aircraft wheels, obtaining wheel speed data associated with the aircraft wheel. The method includes determining, based at least in part on the wheel speed data, deceleration of the aircraft wheel during a time interval, and determining, based at least in part on the determined deceleration, a value indicative of friction associated with the aircraft wheel. The method includes providing, based at least in part on the determined value, a signal indicative of a level of friction associated with the aircraft wheel.

公开(公告)号：US20250042566A1

公开(公告)日：2025-02-06

申请号：US18788352

申请日：2024-07-30

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

Inventor： Umberto Gastaldi ,  Brice Saudel ,  Grégoire Smith ,  Julien Aubry

IPC: B64D33/02 ,  F02C7/042 ,  F02C7/045

Abstract: An air intake that makes it possible to avoid stiffeners and a front frame includes a lip, at least one external panel extending the lip on the outer side, at least one internal panel extending the lip on the inner side, the wall of the air intake having a thickness of value e. The thickness of the wall of the air intake changes longitudinally and comprises a zone at the front longitudinal end having a thickness of value e2 greater than the thickness e. In this way, the thickness of the air intake is optimized according to the needs of the zone concerned. A nacelle and propulsive assembly are provided with such air intake.

公开(公告)号：US20240417066A1

公开(公告)日：2024-12-19

申请号：US18740660

申请日：2024-06-12

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

Inventor： Oliver Family ,  Sébastien Blanc

IPC: B64C13/38 ,  B64C9/02

Abstract: A wing defines a chord which runs from a leading edge to a trailing edge. The wing has a main portion and a flap which is movable relative to the main portion to change the aerodynamics of the wing, for instance to maximize lift, or to reduce drag at the expense of some loss of lift. The wing has a guide mechanism which guides movement of the flap. The guide mechanism uses a pair of runners which run along respective tracks. The tracks are positioned at different locations along the direction of the chord, but overlap one another in the direction of the chord.

公开(公告)号：US20240400223A1

公开(公告)日：2024-12-05

申请号：US18673398

申请日：2024-05-24

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

Inventor： Juan RIVERO SESMA

IPC: B64D45/08

Abstract: A method for assisting landing of an aircraft on a landing runway of a destination airport facility includes two successive determinations of the position of the aircraft with respect to the landing runway and based on a photographic image taken from the aircraft, respectively according to two different algorithms for determining the position of the aircraft, together with the supply of at least one piece of information representative of a difference between the two determined positions. It is thus possible to verify whether the destination landing runway observed from the photographic image taken from the aircraft is indeed the target destination runway on which a landing of the aircraft is planned, or whether there exists an error in positioning of the aircraft with respect to the destination landing runway.

公开(公告)号：US20240393926A1

公开(公告)日：2024-11-28

申请号：US18664644

申请日：2024-05-15

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

Inventor： Benjamin Mazoin

IPC: G06F3/04842 ,  G06F3/04812

Abstract: A display on a screen of human-machine interface of a cockpit of an aircraft includes a text entry region, a navigation chart region, and at least one other region. A specific pointing mode, active when text entry is in progress, and a normal pointing mode, active at all other times, are implemented. In normal pointing mode, a pointing action triggers the command if any associated with the location where the pointing action is carried out. In specific pointing mode, only a pointing action in the text entry region or in the navigation chart region triggers a command if any associated with the location where the pointing action is carried out, while a pointing action in the at least one other region triggers an abandonment of text entry. Thus, tasks requiring a pilot of the aircraft to enter text are simplified.

公开(公告)号：US12110093B2

公开(公告)日：2024-10-08

申请号：US17982999

申请日：2022-11-08

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

Inventor： Benoit Orteu ,  Ludovic Mil ,  Lionel Laganier ,  Dominique Marty ,  Philippe Robert

IPC: B64C1/20

CPC classification number: B64C1/20

Abstract: An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.