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公开(公告)号：US20230406486A1
公开(公告)日：2023-12-21
申请号：US18337897
申请日：2023-06-20
发明人： Fraser WILSON , Benjamin BISHOP
摘要： A trailing link landing gear (6) has a main arm (20) which extends from a proximal end (22) attachable to an aircraft (2) to a distal end (24), and a trailing arm (30) which extends from a pivotable connection at the distal end (24) of the main arm (20) to one or more wheels (39). A shock absorber (40) extends between the main arm (20) and the trailing arm (30). An adjustment member (50) mounted to one of the arms can be moved to move an end of the shock absorber (40) and thereby change the angle that the trailing arm (30) makes with the main arm (20). This, in turn, changes the height of the landing gear (6) and in doing so changes the angle of attack (10) of an aircraft (2) including the landing gear (6).
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公开(公告)号：US20230356830A1
公开(公告)日：2023-11-09
申请号：US18011939
申请日：2021-06-21
发明人： Sébastien DUBOIS
摘要： A locking device locks a landing gear mounted in rotation on an aircraft and includes a deployment hydraulic jack including a first chamber connected to a first hydraulic supply and a second chamber connected to a second hydraulic supply. The locking device includes a hydraulic actuator connected to a rotary distributor. The rotary distributor includes a coupling operationally connecting the rotary distributor to a strut of the landing gear, a first supply port fluidly connected to the first hydraulic supply, and a first outlet port fluidly connected to the hydraulic actuator.
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公开(公告)号：US11614103B2
公开(公告)日：2023-03-28
申请号：US17435675
申请日：2020-03-02
发明人： Takaaki Onishi , Shogo Hagihara
摘要： A landing gear lifting/lowering EHA system includes: a hydraulic actuator configured to lift and lower the leg of an aircraft; at least one electrically operated hydraulic pump; a hydraulic path; a pressure sensor attached to the hydraulic actuator or the hydraulic path and configured to output a measurement signal corresponding to hydraulic pressure; and a controller configured to output a control signal to the electrically operated hydraulic pump, wherein, when a state in which the hydraulic pressure exceeds a set pressure continues for a set time, the control unit stops the electrically operated hydraulic pump in operation and resumes the operation of the electrically operated hydraulic pump after the hydraulic pressure drops to or below a second set pressure after the electrically operated hydraulic pump is stopped.
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公开(公告)号：US11548623B2
公开(公告)日：2023-01-10
申请号：US17055816
申请日：2019-05-16
发明人： Robert Ian Thompson
摘要： An aircraft landing gear is disclosed having a first oleo strut include a sleeve portion and a slider portion, the slider portion being slidable within a hydraulic fluid chamber of the sleeve portion, and a second, similar oleo strut. The landing gear also includes a hydraulic fluid balancer having a balance chamber separated into first and second end sections, wherein the hydraulic fluid chamber of the sleeve portion of the first oleo strut is fluidly connected to the first section of the balance chamber and the hydraulic fluid chamber of the sleeve portion of the second oleo strut is fluidly connected to the second section of the balance chamber of the hydraulic fluid balancer.
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公开(公告)号：US20220281591A1
公开(公告)日：2022-09-08
申请号：US17195404
申请日：2021-03-08
申请人： GOODRICH CORPORATION
发明人： Jason Bradley Allen
摘要： A nose-wheel steering system may comprise an actuator and a bevel gear rotationally coupled to a drive shaft of the actuator. The bevel gear may be configured to rotate about a first axis. A collar gear may be intermeshed with the bevel gear. The collar gear may be configured to rotate about a second axis that is generally perpendicular to the first axis.
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公开(公告)号：US11414181B2
公开(公告)日：2022-08-16
申请号：US16221948
申请日：2018-12-17
发明人： Neil Richard Price
摘要： An aircraft landing gear assembly includes a bi-stable, split line tube biased to assume a tubular condition to serve in place of a lock link or side stay and a flexible vessel actuator configured to radially enlarge the tube at a region for folding.
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公开(公告)号：US11358710B2
公开(公告)日：2022-06-14
申请号：US15904003
申请日：2018-02-23
申请人： The Boeing Company
发明人： Leo W. Plude , Malcolm S. Bryant
摘要： Methods and apparatus for controlling landing gear retract braking are described. A controller is to determine an on-ground status of a wheel of a landing gear. The controller is to generate a control signal based on the on-ground status of the wheel. The control signal is to initiate a retract braking process for the wheel. The retract braking process is to decelerate the wheel from a first rate of rotation to a second rate of rotation less than the first rate of rotation.
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公开(公告)号：US11186360B2
公开(公告)日：2021-11-30
申请号：US16713525
申请日：2019-12-13
申请人： The Boeing Company
摘要： Methods of retracting a strut assembly for stowing aircraft landing gear comprise longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position by pressurizing an upper bulkhead space between an upper plate of the upper bulkhead and an upper bulkhead restriction structure that is fixed to the upper tubular housing. Other methods of retracting a strut assembly for stowing aircraft landing gear comprise flowing liquid from an upper liquid chamber positioned above an upper bulkhead within an upper tubular housing to a recoil chamber, wherein during the flowing, the liquid is prevented from passing from the recoil chamber to a pressure chamber that is defined between the upper bulkhead and a lower bulkhead, thereby longitudinally translating a lower tubular housing upward.
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公开(公告)号：US11142305B2
公开(公告)日：2021-10-12
申请号：US16265041
申请日：2019-02-01
发明人： Daniel Moine , Hervé Rolinat
摘要： An aircraft undercarriage having a leg for mounting to move on an aircraft structure between a deployed position and a retracted position is provided. The undercarriage generally includes a brace member arranged between the structure of the aircraft and the leg in order to stabilize the leg in the deployed position, and a drive actuator for moving the leg from the deployed position to the retracted position. The brace member includes a strut arm having a proximal end that is designed to be hinged on the structure of the aircraft. The arm presents a longitudinal slot extending until the slot reaches a distal end in order to terminate in a bend and having slidably engaged therein a finger that is secured to the leg, the drive actuator being coupled to the strut arm.
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公开(公告)号：US11130564B2
公开(公告)日：2021-09-28
申请号：US15851169
申请日：2017-12-21
申请人： GOODRICH CORPORATION
发明人： William E Luce , Adam J. Ditzler
摘要： Systems and methods for enabling aircraft shock strut shrink are provided. The system may comprise a shock strut comprising a shrink piston, an accumulator comprising a gas piston and a hydraulic chamber, wherein the gas piston is configured to apply gas pressure to the hydraulic chamber, and a first valve in fluid communication with the accumulator. The system may further comprise a second valve, wherein the second valve is in fluid communication with a vent, the pneumatic cylinder, and the gas piston, wherein the first valve is in fluid communication with the hydraulic chamber and the shrink piston.
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