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公开(公告)号：WO2022207437A1
公开(公告)日：2022-10-06
申请号：PCT/EP2022/057730
申请日：2022-03-24
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： IYENGAR, Parthasarathy
IPC: B64C1/00 , B64C2001/0072 , B64F5/60 , G01N2203/0066 , G01N3/02 , G01N3/08 , G01N3/56 , G01N3/62
Abstract: A first aspect of the present invention provides a load-bearing structure configured to, during operation of the structure, transfer load from a first part of the structure to a second part of the structure via a load path. The component comprises a matrix material, a plurality of longitudinal first reinforcing elements embedded in the matrix material, and a plurality of longitudinal second reinforcing elements embedded in the matrix material. The long axis of each first reinforcing element is substantially aligned with a first direction and the long axis of each second reinforcing element is substantially aligned with a second direction, the second direction being substantially perpendicular to the first direction. The structure has a predefined crack-propagation region configured to control the propagation of a crack in the structure. The crack-propagation region either comprises multiple first reinforcing elements and does not comprise any second reinforcing elements; or comprises multiple second reinforcing elements and does not comprise any first reinforcing elements.
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公开(公告)号：WO2022180355A1
公开(公告)日：2022-09-01
申请号：PCT/GB2022/050330
申请日：2022-02-08
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： TULLOCH, William
Abstract: An aircraft wing comprising: a wingbox; a fuel tank; a fuel cell system comprising a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.
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公开(公告)号：WO2022129276A1
公开(公告)日：2022-06-23
申请号：PCT/EP2021/086082
申请日：2021-12-16
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： BILL, Andrew
Abstract: There is provided a sensor device for use in determining at least one property of a wheel assembly comprising a tire mounted on a wheel. The sensor device is configured to be attachable to an outer circumferential surface of the wheel which faces an inner circumferential surface of the tire. The sensor device is configured to measure a distance between the sensor device and an object remote from the sensor device.
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公开(公告)号：WO2021180505A1
公开(公告)日：2021-09-16
申请号：PCT/EP2021/055049
申请日：2021-03-01
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： BIRD, James , PALMER, Scott , O'SHAUGHNESSY, Paul , BRYANT, Anthony
Abstract: Disclosed is an electrical connection apparatus for providing an electrical connection between a first structure of an aircraft system and a second structure of an aircraft system, the second structure movable relative to the first structure. The electrical connection apparatus has a female connector, and a male connector at least partially housed within the female connector such that telescoping motion is enabled between the male and female connectors. The male and female connectors have respective electrical contacts that are contactable with one another. The male and female connectors have respective constant radii of curvature along their respective lengths, and the constant radii of curvature share a common centre of curvature.
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公开(公告)号：WO2021170450A1
公开(公告)日：2021-09-02
申请号：PCT/EP2021/053716
申请日：2021-02-16
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： TULLOCH, William , BROOMFIELD, Pat
Abstract: There is provided an aircraft assembly comprising a wing component and an engine mounting pylon component. The wing component comprises three fastening locations arranged in a triangle such that they define a plane. The engine mounting pylon component is connected to the wing component by three tension fasteners, wherein each of the tension fasteners passes through a different one of the fastening locations. The wing component comprises three first spherical surfaces positioned such that the centre of each first spherical surface is at a different one of the fastening locations. The engine mounting pylon component comprises three second spherical surfaces having equal and opposite curvature to the first spherical surfaces. Each of the second spherical surfaces is in contact with a different one of the first spherical surfaces.
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Patent Agency Ranking
公开(公告)号：WO2021151693A1
公开(公告)日：2021-08-05
申请号：PCT/EP2021/050892
申请日：2021-01-18
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： HEALY, Daren , CUSTANCE, Denys
IPC: B64C23/06
Abstract: An apparatus includes an outlet configured to output hot air, a flow control device movable between a first position and a second position, and a phase change actuator. The phase change actuator is connected to the flow control device and configured to move the flow control device between the first position and the second position at a predetermined temperature where a change of phase of a working substance of the phase change actuator occurs. In the second position, the flow control device may be configured to interact with an airflow and/or the hot air so as to protect a structure downstream of the outlet from overheating. The flow control device may be a vortex generator. In the second position, the vortex generator may be configured to interact with an airflow and/or the hot air from the outlet so as to redirect and/or reduce the temperature of the hot air.
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公开(公告)号：WO2021148336A1
公开(公告)日：2021-07-29
申请号：PCT/EP2021/050887
申请日：2021-01-18
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： THOMPSON, Robert
IPC: B64C1/00 , B64C7/00 , B64D37/04 , B64D37/06 , B64C1/0009 , B64C2001/0045
Abstract: An aircraft comprising: a fuselage having a pressure shell, a fairing, and an unpressurised space between the pressure shell and the fairing. One or more fuel lines extend inside the unpressurised space from the fuel tank to an engine. The fairing may have a window in line with a window of the pressure shell. The fuel tank may be configured to carry a cryogenic fuel such as liquid hydrogen.
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公开(公告)号：WO2021094170A1
公开(公告)日：2021-05-20
申请号：PCT/EP2020/080998
申请日：2020-11-04
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： EDWARDS, Henry , MACGREGOR, Keith
Abstract: The present invention relates to an aircraft (100) comprising an active drag control system such as a Laminar Flow Control (LFC) system having a port LFC apparatus (118) and a starboard LFC apparatus (120). The aircraft comprises a control system (126) that is configured to test how efficiently the LFC system is working by differentially operating the port LFC apparatus (118) and the starboard LFC apparatus (120), for example by deactivating either LFC apparatus (118, 120), and measuring the effect on the direction of flight of the aircraft (100). The control system (126) is also configured to change the direction of the aircraft (100), and trim the aircraft (100), by differentially operating the port LFC apparatus (118) and the starboard LFC apparatus (120)..
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公开(公告)号：WO2021078546A1
公开(公告)日：2021-04-29
申请号：PCT/EP2020/078530
申请日：2020-10-12
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： BIDMEAD, Ashley , BECHER, Florian
Abstract: Disclosed is an aircraft system (10) for an aircraft (1), the aircraft system (10) having a controller (100) that is configured to receive at least one signal during a landing procedure of the aircraft (1) and to determine that the aircraft (1) is at a predetermined stage in the landing procedure, on the basis of the at least one signal. The predetermined stage in the landing procedure is before a command to extend at least one landing gear (600) of the aircraft (1) is issued during the landing procedure. The controller (100) is configured to cause initiation of at least a part of a procedure to interrogate an aircraft braking system (200), on the basis of the determination.
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公开(公告)号：WO2021058349A1
公开(公告)日：2021-04-01
申请号：PCT/EP2020/075864
申请日：2020-09-16
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： COOPER, Jonathan , GADD, Matthew
Abstract: There is provided a component life prediction system configured to predict the remaining life of a consumable component installed on an aircraft. The system comprises a processor configured to: receive wear information indicative of a current wear state of the component; receive schedule information indicative of a future flight schedule for the aircraft; and determine the remaining life of the component based on the received wear information and the received schedule information.
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