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公开(公告)号：WO2021032656A1
公开(公告)日：2021-02-25
申请号：PCT/EP2020/072950
申请日：2020-08-17
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： TULLOCH, William , BROOMFIELD, Pat
Abstract: A first aspect of the present invention provides an aircraft assembly comprising a wing and an engine mounting pylon. An aft end of the engine mounting pylon is connected to the wing by a spigot and at least one fastener. The aircraft assembly is configured such that, during operation of the aircraft assembly on an aircraft, the spigot transfers only lateral load between the engine mounting pylon and the wing and the at least one fastener transfers only vertical load between the engine mounting pylon and the wing.
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公开(公告)号：WO2018197120A1
公开(公告)日：2018-11-01
申请号：PCT/EP2018/057353
申请日：2018-03-22
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： HUI, Ching-Yu , MANN, Alan
Abstract: An aerodynamic body for use on an aircraft is presented. The aerodynamic body includes at least a first perforated surface portion (25) and an ice-protection system (31). The first perforated surface portion (25) has perforations, the ice-protection system (31) includes an actuatable element (33) and the actuatable element (33) is movable or deformable between a first position and a second position. In the first position at least a section of the actuatable element (33) is thermally coupled to the first perforated surface portion (25) and configured to prevent an inflow or outflow between a boundary layer of an outer aerodynamic airflow and the aerodynamic body through at least one of the perforations. In the second position at least a section of the actuatable element (33) is distanced from the first perforated surface portion (25) and configured to allow an inflow from a boundary layer of an outer aerodynamic airflow through at least one of the perforations into the aerodynamic body.
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公开(公告)号：WO2018087128A1
公开(公告)日：2018-05-17
申请号：PCT/EP2017/078571
申请日：2017-11-08
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： POWER, Joseph , GAUD, Sebastien , PAVIOUR, David , HEAL, Bradley , WILSON, Fraser
Abstract: Disclosed is an apparatus for dissipating braking energy generated by the operation of a vehicle brake. The apparatus comprises a heating element configured to receive electric current generated by operation of the vehicle brake, the heating element arranged in a chamber for containing liquid. The apparatus is configured such that liquid contained in the chamber is heated in response to operation of the vehicle brake.
Abstract translation: 公开了一种用于消散由车辆制动器的操作产生的制动能量的装置。 该设备包括加热元件，该加热元件构造成接收由车辆制动器的操作产生的电流，加热元件布置在用于容纳液体的腔室中。 该装置被配置为使得容纳在腔室中的液体响应于车辆制动器的操作而被加热。
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公开(公告)号：WO2021083822A1
公开(公告)日：2021-05-06
申请号：PCT/EP2020/080001
申请日：2020-10-26
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： KELLY, Mark
Abstract: An aircraft wing (2) having a main wing (3) and a trailing edge flight control surface (4) movable between a retracted position, a first extended position in which the control surface is positioned rearwardly in the chord wise direction relative to its retracted position, and a second extended position in which the control surface is rotated relative to its retracted position. A closure panel (12), mounted to the main wing (3), extends from the main wing to the control surface (4), to provide an air flow surface between the main wing and control surface, both when the control surface is in its retracted position and its first extended position. The closure panel (12) is movable, relative to the control surface (4), to an open configuration in which it opens an airflow passage (40) provided between the control surface (4) and an opposed surface of the aircraft wing when the control surface (4) is in its second extended position.
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公开(公告)号：WO2020254386A1
公开(公告)日：2020-12-24
申请号：PCT/EP2020/066733
申请日：2020-06-17
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： SHEBLI, Mouayiad
Abstract: The application relates to a pipe support block for an aircraft fluid system. The pipe support block is arranged to support a pipe on a structural member, such as a bracket. The pipe support has a first part and a second part which together form a collar. The collar has a pipe receiving bore and is configured to support a fluid pipe on the structural member. First and second fastener holes extend through both the first part and the second part. The first and second fastener holes are each arranged to receive a fastener to fasten the first and second parts to each other and to the structural member.
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Patent Agency Ranking
公开(公告)号：WO2020239881A1
公开(公告)日：2020-12-03
申请号：PCT/EP2020/064787
申请日：2020-05-28
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： DOBBIN, Richard
Abstract: The present application relates to a spark containment cap. The cap forms a sealed cavity around an end of a fastener protruding from a structure. The cap has a cap body defining an air cavity arranged to enclose the end of the fastener. The cap body includes an annular base (210) terminating at a base rim (211) which surrounds an opening into the air cavity. An annular skirt (230) of the cap provides an annular sealing volume extending around the base rim (211) arranged to receive an annular bead of a curable sealing material around the opening into the cavity to provide a seal between the cap body and the structure to seal a volume of gas within the cavity. The cap body comprises a cap upper arranged to receive at least part of the end of the fastener. The cap upper (220) is positionable so that an axis of the cap upper (220) is offset from an axis of the annular skirt (230).
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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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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：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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