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1.发明授权公开(公告)号：US10589848B2
公开(公告)日：2020-03-17
申请号：US15395058
申请日：2016-12-30
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：US10549847B2
公开(公告)日：2020-02-04
申请号：US15421607
申请日：2017-02-01
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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