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公开(公告)号：US20240294250A1
公开(公告)日：2024-09-05
申请号：US18574569
申请日：2022-06-24
发明人： Nicolas NGUYEN , Thierry BLANPAIN , Bertrand EUZET
IPC分类号： B64C25/20
CPC分类号： B64C25/20
摘要： An aircraft landing gear includes a strut mounted to an aircraft structure and moveable between extended and retracted positions. A bracing member includes a first bracing connecting rod hinged to the aircraft structure and a second bracing connecting rod hinged to the first bracing connecting rod and to the strut. A stabilizing member includes a first stabilizing connecting rod and a second stabilizing connecting rod hinged together. The second connecting stabilizing rod is hinged to the first bracing connecting rod. At least one spring is arranged to be resiliently subjected to a bending force when the hinges of the first and second stabilizing connecting rods move from their aligned position.
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公开(公告)号：US20240278907A1
公开(公告)日：2024-08-22
申请号：US18570500
申请日：2022-06-17
发明人： Nicolas NGUYEN , Bertrand DUBACHER
CPC分类号： B64C25/001 , B64C25/10 , G01B11/26
摘要： An aircraft landing gear includes a stationary element and one or more movable elements which can move relative to the stationary element between a first position and a second position, and one or more shape sensors, connected to an electronic processor arranged to deduce the position of the movable element of the shape of the shape sensor. The shape sensor includes a first section rigidly connected to the stationary element and a second section rigidly connected to the movable element so that the first section and the second section are immobile with respect to the stationary element and the movable element respectively, and are movable relative to one another.
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公开(公告)号：US20230045934A1
公开(公告)日：2023-02-16
申请号：US17794209
申请日：2021-01-20
发明人： Yves COURTOIS DE LOURMEL , Sébastien MESSE , Jean-Baptiste KAMIS , Arnaud LE BRETON , Nicolas NGUYEN
摘要： An actuator includes a body and at least a first offset connection port that is connected to the body by a first duct projecting from the body. The first connection port is mechanically connected to the body at least by first and second struts. The first strut and the second strut extend from the first connection port, respectively, to a first segment of the body and to a second segment of the body that is axially spaced apart from the first segment.
An undercarriage includes such an actuator as its locking or unlocking actuator.-
公开(公告)号：US20240017821A1
公开(公告)日：2024-01-18
申请号：US18031782
申请日：2021-10-14
摘要： An aircraft undercarriage comprising: a leg connected to an aircraft structure to be movable between a deployed position and a retracted position; a brace member for holding the leg in its deployed position and comprising a first rod hinged to the aircraft structure and a second rod hinged to the first link and to the leg; a stabilizer member for holding the first and second rods in an aligned position and comprising a first link and a second link that are hinged to each other, with at least one of them being hinged to the brace member; and a spring for elastically urging the hinges of the first and second links into a generally aligned position.
The spring comprises at least one spring blade arranged to be subjected to an axial compression force when the first and second links leave the generally aligned position.-
公开(公告)号：US20180086440A1
公开(公告)日：2018-03-29
申请号：US15676261
申请日：2017-08-14
IPC分类号： B64C25/50
CPC分类号： B64C25/505
摘要： An aircraft undercarriage having a sliding rod slidably mounted in a strut-leg, and a scissors linkage (4) having one branch (4a) hinged to the strut-leg or to a turning element of a control for steering the sliding rod mounted to turn in the strut-leg, and one branch (4b) hinged to the sliding rod, the branches being hinged to each other by a pivot pin (12), the undercarriage being fitted with a shimmy-attenuator device (10a, 10b) placed on the pivot pin of the shimmy-attenuator, the attenuator device including threshold resilient return means generating a force returning the branches towards a rest position, and at least damping means generating a damping force when the branches move axially along the pivot pin. The attenuator device comprises two modules (10a, 10b) placed on either side of the scissors linkage in order to co-operate with the pivot pin, each of the modules performing at least one of the damping function and the threshold resilient return function.
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公开(公告)号：US20220266993A1
公开(公告)日：2022-08-25
申请号：US17626342
申请日：2020-07-10
IPC分类号： B64C25/58
摘要： A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.
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