-
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.
-
公开(公告)号：US20230294843A1
公开(公告)日：2023-09-21
申请号：US18121288
申请日：2023-03-14
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： David MARLES
Abstract: A sensor and method for sensing gas absorbed in hydraulic fluid in an aircraft shock absorber are disclosed. The hydraulic fluid and a gas are in fluid communication with each other. The sensor may be incorporated in the shock absorber or in servicing apparatus such as a servicing cart. The amount of gas absorbed in the hydraulic fluid is provided as a parameter which in combination with other parameters allows a user an improved means to determine the maintenance state of the shock absorber and to derive servicing actions.
-
公开(公告)号：US20180362151A1
公开(公告)日：2018-12-20
申请号：US16009470
申请日：2018-06-15
Applicant: Airbus Operations Limited
Inventor： David MARLES
Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.
-
公开(公告)号：US20160348701A1
公开(公告)日：2016-12-01
申请号：US15165429
申请日：2016-05-26
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： David MARLES
CPC classification number: F15B15/22 , B64C25/22 , B64C25/24 , F15B21/065
Abstract: The present invention provides an actuator comprising an actuator body, a piston relatively moveable within the actuator body, and a rod attached to the piston and extending out of the actuator body, the actuator body comprising a port for conveying actuator fluid, wherein the actuator also has a damping control portion provided with damping control fluid containing magnetic particles, wherein the piston or the rod is adjacent the damping control fluid, and a first electrical coil associated with the damping control portion, such that an electrical current supplied to the first electrical coil induces a magnetic field and causes the effective viscosity of the damping control fluid to increase, thus increasing the damping effect of the damping control fluid on the piston or rod. The invention also provides an aircraft assembly, such as a landing gear assembly, an aircraft and a method of operating an actuator.
Abstract translation: 本发明提供了一种致动器，其包括致动器主体，在致动器主体内可相对移动的活塞，以及连接到活塞并延伸出致动器主体的杆，致动器主体包括用于输送致动器流体的端口，其中致动器还 具有阻尼控制部分，设置有包含磁性颗粒的阻尼控制流体，其中活塞或杆与阻尼控制流体相邻，以及与阻尼控制部分相关联的第一电线圈，使得提供给第一电线圈的电流 引起磁场并且使阻尼控制流体的有效粘度增加，从而增加阻尼控制流体对活塞或杆的阻尼作用。 本发明还提供一种飞机组件，例如起落架组件，飞行器和操作致动器的方法。
-
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.
-
Patent Agency Ranking
公开(公告)号：US20220258854A1
公开(公告)日：2022-08-18
申请号：US17736787
申请日：2022-05-04
Applicant: Airbus Operations Limited.
Inventor： David MARLES
Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.
-
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
-
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.
-
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.
-
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.
-
-
-
-
-
-
-
-
-
Search Results
10
records
(took 0.013 seconds)
