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公开(公告)号：US20230234700A1
公开(公告)日：2023-07-27
申请号：US18009260
申请日：2021-06-10
CPC分类号： B64C25/405 , B64C25/34 , B64C25/42 , B64C25/60 , B64C2025/008
摘要： A landing gear of an aircraft having an upper portion intended to be joined to a structure of the aircraft and a lower portion provided with a first and second axle, the first axle being provided with a braked wheel and the second axle being provided with a motorised wheel, includes a first actuator that moves one of the axles between remote and close positions with respect to the upper portion while the other axle is kept stationary with respect to the upper portion. In one of the remote and close positions, and the wheels on the axles are simultaneously in contact with a running surface while, in the other position, each wheel on the second axle is at a distance from said running surface.
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公开(公告)号：US20240199202A1
公开(公告)日：2024-06-20
申请号：US18565017
申请日：2022-05-25
CPC分类号： B64C25/405 , B64C2025/008
摘要： An aircraft has an upper portion and a lower portion provided with a first and second axle. The first axle is provided with a braked wheel and the second axle is provided with a motorized wheel. A landing gear of the aircraft includes a main arm pivoting with respect to the strut on which the first axle is fixed. The second axle is fixed on the strut, and a main actuator moves the first axle between a remote position and a close position with respect to the upper portion. In the close position, the braked and motorized wheels are simultaneously in contact against a running plane, and in the remote position, the braked wheels are in contact against the running plane while the motorized wheel is at a distance from the running plane.
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3.发明申请公开(公告)号：US20180111678A1
公开(公告)日：2018-04-26
申请号：US15395058
申请日：2016-12-30
CPC分类号： B64C25/62 , B64C25/34 , B64C25/50 , B64C25/505
摘要： A landing-gear assembly (1) for an aircraft, the landing-gear assembly comprising: an axle shaft (2); a leg (3) presenting a first portion (3a) carrying said axle shaft (2) and a second portion (3b) connected to a carrier structure of the aircraft; a main damper (5); and a first secondary damper (6a) distinct from the main damper (5). The first secondary damper (6a) is carried by the axle shaft (2) and comprises: an inertial mass (M); and connection means (7a) between the inertial mass (M) and the axle shaft (2) damping movements of the inertial mass (M) along a first axis (X1) of movement of the inertial mass (M) relative to the axle shaft (2), said first axis of movement (X1) extending in a plane (P) perpendicular to said steering axis (Z).
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公开(公告)号：US20180044001A1
公开(公告)日：2018-02-15
申请号：US15421607
申请日：2017-02-01
IPC分类号： B64C25/50
摘要： Aircraft landing gear (1) comprising: an axle shaft (2); a strut (3) extending along a main strut axis (Z) and having a first part (3a) carrying the said axle shaft (2) and a second part (3b); a main damper (5) designed to damp axial movements of the first strut part (3a) with respect to the second strut part (3b); a first secondary damper (6a) distinct from the said main damper and designed to damp a movement of angular oscillation, about the axis (Z). The first secondary damper (6a) is carried by the first strut part (3a) and comprises: an inertial mass (M); and means (7a) of connecting the inertial mass (M) to the first strut part (3a) which means are designed to damp rotational movements of this inertial mass (M) about the axis (Z).
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