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公开(公告)号：WO2010007415A3
公开(公告)日：2010-01-21
申请号：PCT/GB2009/050844
申请日：2009-07-14
Applicant: AIRBUS OPERATIONS LIMITED , WINTER, Darren John
Inventor： WINTER, Darren John
Abstract: A stiffener (24) has an elongate web (30) element and at least one elongate foot element (28), the web element and foot element being connected by a curved elbow, wherein the radius of the curved elbow is greater over a first portion (C) of the stiffener than over a second portion (E) of the stiffener. A roll forming die (32) comprises first (34) and second (36) rollers, the first roller having a shaped section arranged to be located within a correspondingly shaped recess in the circumferential surface of the second roller, the first and second rollers defining a gap (40) there between corresponding to the desired shape to be imparted on an elongate member (20) passed between the rollers, the desired shape including a curved elbow between a web and a foot portion, wherein the shape of the recess in the second roller and the shape of the corresponding section of the first roller vary around a portion of the rollers circumference such that the radius of curvature of the gap between the rollers corresponding to the curved elbow varies between a minimum and a maximum value. The stiffener is formed by feeding an elongate member through the roll forming die and rotating the die rollers between a first and a second position as a portion of the elongate member is fed between the die rollers, whereby the radius of the curved elbow formed in the stiffener is varied.
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公开(公告)号：WO2022129143A1
公开(公告)日：2022-06-23
申请号：PCT/EP2021/085847
申请日：2021-12-15
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： BILL, Andrew
IPC: B60C23/04
Abstract: Checking the operating parameters of a tyre, such as tyre pressure, is an important part of tyre maintenance, particularly in aircraft. A tyre monitor (11) comprises a sensor device (12) arranged to detect an operating parameter of a tyre and a protective housing (14) for the device, the device being retained on a ring (15) having spaced end portions (16a, 16b), the ring being resiliently radially biased. The provision of a retaining ring facilitates installation of the tyre monitor within a tyre assembly, so that the sensor device can directly monitor the operating parameter of the tyre. The protective housing protects the sensor device from impact, vibration and temperature extremes.
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公开(公告)号：WO2021180504A1
公开(公告)日：2021-09-16
申请号：PCT/EP2021/055046
申请日：2021-03-01
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： O'SHAUGHNESSY, Paul , PALMER, Scott , BRYANT, Anthony , BIRD, James
Abstract: An aircraft system has a first structure, and a second structure coupled to the first structure and movable between first and second positions relative to the first structure. The aircraft system has an electrical connector for providing an electrical connection running between respective components housed within the first and second structures. The electrical connector has a cable harness housed within the first structure, and a connector body coupled to an end of the cable harness. The connector body extends through an aperture formed in the first structure, and the connector body is coupled to the second structure such that movement of the second structure between the first and second positions relative to the first structure causes the connector body to move through the aperture.
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公开(公告)号：WO2021151718A1
公开(公告)日：2021-08-05
申请号：PCT/EP2021/051012
申请日：2021-01-19
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： HOWELL, George
Abstract: A method of landing an aircraft, the aircraft comprising a first aircraft, the first aircraft comprising a landing system. The landing system is operated to: receive information from a second aircraft via a direct aircraft-to-aircraft communication from the second aircraft to the first aircraft; determine a landing plan of the first aircraft based on the information; and land the first aircraft based on the landing plan of the first aircraft. The use of a direct aircraft-to-aircraft communication (i.e. a communication from the second aircraft to the first aircraft which does not travel via an intermediary such as a land station, air traffic controller or satellite) makes the method reliable because such a communication is inherently secure and difficult to hack. The first aircraft is a member of a virtual fleet of aircraft. The landing system of the first aircraft is operated to: receive landing plans of all other aircraft of the virtual fleet; and input the landing plans of all other aircraft of the virtual fleet into an optimisation algorithm which determines a set of landing plans for the virtual fleet of aircraft which is optimised for the entire virtual fleet, the optimised set of landing plans for the virtual fleet of aircraft including the landing plan of the first aircraft.
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公开(公告)号：WO2021130063A1
公开(公告)日：2021-07-01
申请号：PCT/EP2020/086222
申请日：2020-12-15
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： JACKSON, Anthony , REDMAN, Michael , LAND, Patrick , PAYNE-DWYER, Chris , CLOUGH, Andrew
IPC: G01N23/203 , B23Q17/22 , B64F5/00 , B23Q17/2233 , G01V5/0025
Abstract: An apparatus and method for adjusting the position of a tool relative to a component using an x-ray backscatter device, including an x-ray backscatter device that is positioned adjacent a first side of a component and configured to emit x-rays towards the component and receive backscattered x-rays. A computer receives information relating to the backscattered x-rays from the x-ray backscatter device. A tool is located adjacent the first side of the component, and is moved to a position adjacent the first side of the component based on a datum determined from the information received by the computer determined datum.
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Patent Agency Ranking
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：WO2021063830A1
公开(公告)日：2021-04-08
申请号：PCT/EP2020/076916
申请日：2020-09-25
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： HOWELL, George
Abstract: Disclosed is test apparatus (100) for testing at least part of an aircraft system. The test apparatus (100) is configured to obtain first data (210) comprising a plurality of input values and process the input values using a classifier (230) configured to model an operation of the at least part of an aircraft system (220). Second data is obtained, comprising a set of output values (240b). The output values (240b) from the second data are processed with output values (240a) generated by the classifier to identify differences between operation of the at least part of an aircraft system (220) and the operation as modelled by the classifier (230).
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公开(公告)号：WO2021047980A1
公开(公告)日：2021-03-18
申请号：PCT/EP2020/074507
申请日：2020-09-02
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： SHARPE, Peter
Abstract: Retraction of a landing gear assembly (4) on an aircraft (1) is actuated by a hydraulic actuator (12). The actuator (12) includes a piston (28) that travels within a cylinder (26) along a stroke length between a first position corresponding to the landing gear assembly when extended and a second position corresponding to the landing gear assembly when retracted. Movement of the piston (28) along its stroke length is snubbed at one end by a different amount according to the direction of travel, for example by use of an orifice plate (Fig 10; Fig 11) that has a discharge coefficient that is greater in one direction (Fig 13) than in the opposite direction (Fig 12). Asymmetric snubbing is thus provided, which enables the landing gear to retract faster.
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公开(公告)号：WO2021023618A1
公开(公告)日：2021-02-11
申请号：PCT/EP2020/071529
申请日：2020-07-30
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： OLIVEIRA, Hugo , RIBEIRO, Victor
IPC: G05B19/042 , G05B23/02 , B60T7/04 , B60T17/22 , B60T8/17
Abstract: Disclosed is an avionics unit for an aircraft. The unit comprises a communications interface arranged to interface with one or more other avionics units. The communication interface is arranged to transmit a signal having a first state indicating a fault condition of the avionics unit to the one or more other avionics units if the first state persists for a predetermined time. A processor is arranged to modulate an output at the communication interface to provide a modulated signal to indicate a characteristic of a present state of the avionics unit with respect to the fault condition. The modulated signal comprising the first state and a second state, different from the first state, wherein, in the modulated signal, the first state has a duration less than the predetermined time
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公开(公告)号：WO2020260269A1
公开(公告)日：2020-12-30
申请号：PCT/EP2020/067478
申请日：2020-06-23
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： KERR, Sean , MARLES, David
Abstract: Disclosed is a method of operating a landing gear controller for an aircraft. The method comprises the landing gear controller receiving one or more signals from at least one position sensor. The one or more signals indicate a position of one of a landing gear bay door and a landing gear when the landing gear bay door or the landing gear, respectively, is part way through a range of travel between two limits of travel. The method also comprises the landing gear controller controlling movement of the other of the landing gear bay door and the landing gear on the basis of the one or more signals.
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