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公开(公告)号：US20220135213A1
公开(公告)日：2022-05-05
申请号：US17435355
申请日：2020-06-23
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Sean KERR , David MARLES
Abstract: A method of operating a landing gear controller for an aircraft, including: 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 may also include 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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公开(公告)号：US20210291966A1
公开(公告)日：2021-09-23
申请号：US17319722
申请日：2021-05-13
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Sean KERR , David MARLES , Paul Gordon L'ALLIER
Abstract: A single acting actuator for an aircraft landing gear assembly is disclosed having a piston mounted in a cavity and moveable relative to a housing between a retracted position and an extended position, the piston dividing the cavity into first and second pressure chambers. At least one of the pressure chambers is associated with first and second outlets, with the actuator being arranged such that, in respect of the relative movement in which the pressure chamber is the decreasing volume pressure chamber, in a first stage of the relative movement the first and second outlets are open thereby allowing actuator fluid to flow out of the pressure chamber through the first and second outlets and in a second stage of the relative movement the second outlet is open but the first outlet is closed, thereby acting to slow the relative movement of the piston with respect to the housing.
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公开(公告)号：US20200277044A1
公开(公告)日：2020-09-03
申请号：US16799896
申请日：2020-02-25
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Sean KERR , David MARLES
Abstract: An aircraft landing gear control system 1000 configured to be operably connected to one or more landing gear systems 30, 40 of an aircraft. The aircraft landing gear control system includes a controller 20 configured to: send at least one output for initiating operation of the one or more landing gear systems; determine whether at least one landing gear system of the one or more landing gear systems has failed to operate correctly in response to the at least one output; and determine at least one remedial action to be taken, when the controller determines that the at least one landing gear system has failed to operate correctly.
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公开(公告)号：US20250153845A1
公开(公告)日：2025-05-15
申请号：US18938054
申请日：2024-11-05
Applicant: Airbus Operations Limited
Inventor： Sean KERR , Mark JOHNSON
IPC: B64C25/26
Abstract: A landing gear controller that: determines whether a predetermined criterion is met; and causes a power supply system of an aircraft to supply power to an actuation system of the aircraft to cause a component of a landing gear system of the aircraft to move from a first position to a second position selectively according to: a first predetermined supplied-power profile, when the landing gear controller determines that the predetermined criterion is not met, and a second predetermined supplied-power profile, according to which a maximum power supplied by the power supply system to the actuation system is greater than a maximum power supplied by the power supply system to the actuation system according to the first predetermined supplied-power profile, to move the component from the first position to the second position more quickly, when the landing gear controller determines that the predetermined criterion is met.
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公开(公告)号：US20220194564A1
公开(公告)日：2022-06-23
申请号：US17604272
申请日：2020-08-25
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Paul L'ALLIER , Andy MOUNTY , Sean KERR
IPC: B64C25/22 , B64C25/16 , F15B11/024 , F15B15/18
Abstract: An aircraft hydraulic actuation system for retracting an aircraft landing gear. The actuation system includes a supply line arranged to carry hydraulic fluid pressurized by a pump, a return line arranged to return hydraulic fluid to a reservoir, and a hydraulic actuator 128. In a first mode of operation, a first chamber 130 of the actuator 128 is supplied with pressurized hydraulic fluid from the supply line such that a piston 134 is moved in a first direction so as to move a load such as a landing gear. In a second mode of operation, the first chamber 130 is taken out of fluid communication with the supply line and a second chamber 132 is in fluid communication with the return line, such that the piston 134 is able to be moved under the influence of the load, for example when the landing gear extends under gravity.
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Patent Agency Ranking
公开(公告)号：US20200277043A1
公开(公告)日：2020-09-03
申请号：US16799920
申请日：2020-02-25
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Sean KERR , David MARLES
IPC: B64C25/26
Abstract: An aircraft control system 100 operably connected to a landing gear and a landing gear bay door of an aircraft 400. The system includes: a user interface 10 to receive manual inputs of first and second requests and a landing gear controller 20 configured to: receive a first indication indicative of user-operation of the user interface to input the first request, and to initiate movement of the landing gear bay door from a closed position to an open position on the basis of the first indication without initiating movement of the landing gear between an extended position and a retracted position; and receive a second indication indicative of user-operation of the user interface to input the second request, and to initiate movement of the landing gear between the extended position and the retracted position on the basis of the second indication.
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公开(公告)号：US20250108911A1
公开(公告)日：2025-04-03
申请号：US18889012
申请日：2024-09-18
Applicant: Airbus Operations Limited
Inventor： Sean KERR , Mark JOHNSON
Abstract: A computer-implemented method that includes receiving information indicative of an aircraft steering angle of an aircraft, comparing the received information against a threshold above which degradation of a tire of a landing gear of the aircraft is expected to occur and causing an action to be performed based on a result of the comparison. Also an aircraft system.
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公开(公告)号：US20240199201A1
公开(公告)日：2024-06-20
申请号：US18520151
申请日：2023-11-27
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Sean KERR
Abstract: A method of extending a landing gear of an aircraft is disclosed. The aircraft includes an uplock arranged to retain the landing gear in a retracted position, a primary landing gear system configured to retract and extend the landing gear, and an alternate landing gear system, independent from the primary landing gear system. The method includes the primary landing gear system holding the landing gear in place while the uplock is moved from a first configuration to a second configuration by the alternate landing gear system.
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公开(公告)号：US20220340267A1
公开(公告)日：2022-10-27
申请号：US17760940
申请日：2020-09-16
Applicant: Airbus Operations Limited
Inventor： Sean KERR , David MARLES
Abstract: An system (10) for an aircraft (1) including a controller (100) configured to receive at least one signal during a take-off procedure of the aircraft. The signal includes information representative of at least one parameter of the aircraft. The controller is configured to determine whether a current or future aircraft climb rate associated with the take-off procedure meets a criterion, on the basis of the at least one signal. The controller is configured to determine at least one remedial action to be taken, such as performance of at least a portion of a procedure to retract a landing gear of the aircraft, when the controller determines that the aircraft climb rate does not meet the criterion.
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公开(公告)号：US20200277042A1
公开(公告)日：2020-09-03
申请号：US16799904
申请日：2020-02-25
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Sean KERR , David MARLES
Abstract: A landing gear system 100 for an aircraft including: a landing gear 130 that is movable between an extended position and a retracted position, the landing gear includes an extendible strut 136; a position sensor 140 configured to detect a position of a part of the extendible strut and output a signal indicative of the position; and a landing gear controller 150 that is communicably connected to the position sensor and is configured, in use, to: receive the signal from the position sensor; and, on the basis of the signal, determine that the strut has extended and the landing gear is in contact with the ground and automatically cause performance of at least a portion of a procedure to move the landing gear from the extended position to the retracted position
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