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1. 发明授权

EP3632794B1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
公开(公告)号：EP3632794B1
公开(公告)日：2020-10-28
申请号：EP19196441.0
申请日：2018-09-26
申请人： Safran Landing Systems UK Limited
发明人： Bennett, Ian
IPC分类号： B64C25/26 , B64C25/20 , B64C25/14

2. 发明公开

EP3632794A1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
公开(公告)号：EP3632794A1
公开(公告)日：2020-04-08
申请号：EP19196441.0
申请日：2018-09-26
申请人： Safran Landing Systems UK Limited
发明人： BENNETT, Ian
IPC分类号： B64C25/26 , B64C25/14
摘要： An aircraft landing gear assembly (10) having a reinstating geometry in which a lock (26) link can be moved to assume a first locking condition to inhibit movement of a stay (18) when a main strut (12) is in a deployed condition and a second locking condition to inhibit movement of the main strut (12) when in a stowed condition. An auxiliary unlock actuator (40, 52) is arranged to apply an unlocking force to the lock (26) when the lock (26) is holding the main strut (12) in the stowed condition, such that the actuator (40, 52) unlocks the lock (26) from the second locking condition.

3. 发明公开

EP3584158A1 AIRCRAFT LANDING GEAR ASSEMBLY WITH A GROUND LOCK 有权
公开(公告)号：EP3584158A1
公开(公告)日：2019-12-25
申请号：EP19182477.0
申请日：2014-08-29
申请人： Safran Landing Systems UK Limited
发明人： BENNETT, Ian
IPC分类号： B64C25/26 , B64C25/20 , E05D11/10 , F16H25/18 , F16H27/06 , E05B57/00
摘要： A mechanical lock (10) for a vehicle assembly such as an aircraft landing gear assembly. The lock is either pivotally mounted and substantially mass balanced, or part of an aircraft landing gear assembly (30) and arranged to be mechanically operated from the ground by a mechanical actuation device.

4. 发明公开

EP4371876A2 AIRCRAFT LANDING GEAR ASSEMBLY 审中-实审
公开(公告)号：EP4371876A2
公开(公告)日：2024-05-22
申请号：EP24168000.8
申请日：2021-06-28
申请人： Safran Landing Systems UK Limited
发明人： BERTHOUD, Marcelo , GUIMARAES MAIA, Leandro , JUESAS PORTOLES, Jorge
IPC分类号： B64C25/20
CPC分类号： B64C25/12 , B64C25/26 , B64C25/20
摘要： An aircraft landing gear assembly (50, 80) comprising: a first landing gear element (60) movably coupled relative to a second landing gear element (62) to pivot about a pivot axis (PA) between a first condition and a second condition; a cam surface (74) defined by the second landing gear element; and a leaf spring having a first end region and a second end region, the first end region of the leaf spring being coupled to the first landing gear element to move with the first landing gear element and the second end region of the leaf spring comprising a cam follower (72) arranged in moving contact with the cam surface such that the cam follower moves from a first region (R1) of the cam surface to a third region (R3) of the cam surface via a second region (R2) of the cam surface as the first landing gear element pivots about the pivot axis between the first condition and the second condition, wherein the cam surface is shaped such that a distance (RO) between the pivot axis and the cam surface increases between the first region and the second region to define a first gradient and the distance between the pivot axis and the cam surface varies between the second region and the third region of the cam surface to define a second gradient, the second gradient being less steep than the first gradient.

5. 发明公开

EP4140880A1 AIRCRAFT LANDING GEAR ASSEMBLY 审中-实审
公开(公告)号：EP4140880A1
公开(公告)日：2023-03-01
申请号：EP21194061.4
申请日：2021-08-31
申请人： Safran Landing Systems UK Limited
发明人： BENNETT, Ian Robert
IPC分类号： B64C25/12 , B64C25/10
摘要： An aircraft landing gear assembly (50) comprising: a first structural member (52); a second structural member (54) pivotally coupled to the first structural member at an apex pivot point so as to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure and being arranged under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly, the linkage assembly comprising: an arm member (58) pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link (56) pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point the such that, as the first and second structural members move relative to one another from the first angular condition towards the second angular condition, the first control link pivot point moves over centre, though an axis or plane bisecting the apex pivot point and the second control link pivot point.

6. 发明公开

EP4122821A1 AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT 审中-实审
公开(公告)号：EP4122821A1
公开(公告)日：2023-01-25
申请号：EP21186935.9
申请日：2021-07-21
申请人： Safran Landing Systems UK Limited
发明人： BENNETT, Ian Robert
IPC分类号： B64C25/60 , B64C25/20 , F15B15/14 , B64C25/22 , B64C25/26
摘要： An aircraft landing gear shock absorber strut (24) comprising: an outer cylinder (26) having a bore defining an opening; an inner cylinder (28) having a first end region movably coupled within the bore and a second end region which projects out of the opening, the inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition in which the shock absorber strut is compressed and a second condition in which the shock absorber strut is extended, the inner cylinder being biased by a spring force to assume the second condition; a mechanical outstop (OS) arranged to engage an abutment surface of the inner cylinder to limit extension of the shock absorber strut; and a rotatable member defining a threaded surface (TS) configured to drive the out stop axially to move the inner cylinder from the second condition towards the first condition to compress the shock absorber strut, the rotatable member being arranged such that the spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.

7. 发明公开

EP4105121A1 AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT 审中-实审
公开(公告)号：EP4105121A1
公开(公告)日：2022-12-21
申请号：EP21180138.6
申请日：2021-06-17
申请人： Safran Landing Systems UK Limited
发明人： BENNETT, Ian Robert
IPC分类号： B64C25/60 , B64C25/12
摘要： An aircraft landing gear shock absorber strut (50, 70, 80) comprising a damping pin (66, 76, 88) and a flow restricting plate having an orifice through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin or the flow restricting plate is coupled to a separator piston so as to move with the separator piston.

8. 发明公开

EP3875367A1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
公开(公告)号：EP3875367A1
公开(公告)日：2021-09-08
申请号：EP20160347.9
申请日：2020-03-02
申请人： Safran Landing Systems UK Limited , Safran Landing Systems Canada Inc.
发明人： BEVAN, Mark , DANDALEIX, Pierre-Etienne , PORTOLES, Jorge , SCHMIDT, Kyle
IPC分类号： B64C25/58 , B64C25/10 , F16F1/18
摘要： An aircraft landing gear assembly comprises a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.

9. 发明公开

EP4112454A1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
公开(公告)号：EP4112454A1
公开(公告)日：2023-01-04
申请号：EP21181982.6
申请日：2021-06-28
申请人： Safran Landing Systems UK Limited
发明人： BERTHOUD, Marcelo , MAIA, Leandro Guimaraes , PORTOLES, Jorge Juesas
IPC分类号： B64C25/26 , B64C25/20 , B64C25/12
摘要： An aircraft landing gear assembly (50, 80) comprising: a first landing gear element (60) movably coupled relative to a second landing gear element (62) to pivot about a pivot axis (PA) between a first condition and a second condition; a cam surface (74) defined by the second landing gear element; and a leaf spring having a first end region and a second end region, the first end region of the leaf spring being coupled to the first landing gear element to move with the first landing gear element and the second end region of the leaf spring comprising a cam follower (72) arranged in moving contact with the cam surface such that the cam follower moves from a first region (R1) of the cam surface to a third region (R3) of the cam surface via a second region (R2) of the cam surface as the first landing gear element pivots about the pivot axis between the first condition and the second condition, wherein the cam surface is shaped such that a distance (RO) between the pivot axis and the cam surface increases between the first region and the second region to define a first gradient and the distance between the pivot axis and the cam surface varies between the second region and the third region of the cam surface to define a second gradient, the second gradient being less steep than the first gradient.

10. 发明授权

EP2925605B1 LANDING GEAR ASSEMBLY AND METHODS 有权转让
标题翻译： FAHRWERKANORDNUNG UND VERFAHREN
公开(公告)号：EP2925605B1
公开(公告)日：2017-01-04
申请号：EP13798377.1
申请日：2013-11-19
申请人： Safran Landing Systems UK Limited
发明人： PADDOCK, Andrew , EMPSON, Paul
IPC分类号： B64C25/26
CPC分类号： B64C25/26
摘要： A landing gear assembly having a first part movable relative to a second part, and a spring coupled to the first and second parts via first and second anchor points. A lost motion assembly is provided to enable one of the anchor points to translate along one of the parts. As such, the spring extends less as the first part moves relative to the second part than it would if each anchor point was fixed to a respective part.
摘要翻译：一种起落架组件，其具有可相对于第二部分移动的第一部分，以及经由第一和第二锚定点联接到第一和第二部分的弹簧。提供了一个空转组件，以使一个锚定点能够沿其中一个部分平移。因此，如果第一部分相对于第二部分移动，则弹簧的伸长越少，如果每个锚点固定到相应的部分则弹簧的延伸越小。

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