专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

91. 发明公开

EP0265197A3 Locking mechanisms 失效
标题翻译：锁定机构
公开(公告)号：EP0265197A3
公开(公告)日：1989-10-25
申请号：EP87309194.6
申请日：1987-10-19
申请人： Dowty Rotol Ltd.
发明人： Bennett, Ian Robert
IPC分类号： B64C25/26
CPC分类号： B64C25/26
摘要： A locking mechanism for locking an assembly, such as aircraft landing gear, in either of two positions. The mechanism comprises a lockable guide member (5) with a recess (6) therein. The guide member (5) is pivotable between a first orientation in which a part of the assembly is locked in the recess (6) with the assembly in a first position, and a second orientation in which a part of the assembly is locked in the recess (6) with the assembly in a second position. The mechanism further comprises an engaging member (10) which may be mounted on the guide member (5) and which is moveable relative to the recess (6), between a locked position and an unlocked position. In the unlocked position, an actuating means (21) for moving the engaging member (10), has a part (19) which is received within the recess (20) to lock the locking mechanism (15) in position and prevent disengagement from the recess.
摘要翻译：用于将诸如飞机起落架的组件锁定在两个位置中的任何一个中的锁定机构。该机构包括其中具有凹部（6）的可锁定引导构件（5）。引导构件（5）可在第一取向之间枢转，其中组件的一部分被锁定在凹部（6）中，组件处于第一位置，第二取向将组件的一部分锁定在凹槽（6）与组件处于第二位置。所述机构还包括接合构件（10），其可以安装在所述引导构件（5）上并且可相对于所述凹部（6）在锁定位置和解锁位置之间移动。在解锁位置，用于移动接合构件（10）的致动装置（21）具有容纳在凹部（20）内的部分（19），以将锁定机构（15）锁定在适当位置并防止脱离凹槽。

92. 发明授权

EP4112454B1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
公开(公告)号：EP4112454B1
公开(公告)日：2024-04-03
申请号：EP21181982.6
申请日：2021-06-28
发明人： BERTHOUD, Marcelo , GUIMARAES MAIA, Leandro , JUESAS PORTOLES, Jorge
IPC分类号： B64C25/26 , B64C25/20 , B64C25/12

93. 发明公开

EP4282752A3 AIRCRAFT LANDING GEAR ASSEMBLY 审中-实审
公开(公告)号：EP4282752A3
公开(公告)日：2024-02-28
申请号：EP23175076.1
申请日：2023-05-24
申请人： Airbus Operations Limited
发明人： BARSALI, Guilherme
IPC分类号： B64C25/12 , B64C25/20 , B64C25/26 , B64F5/60 , G01M17/04 , G01M99/00 , B64C25/22
摘要： A retractable landing gear assembly for an aircraft has a main strut (210) arranged to pivot between a retracted position and an extended position, and a sidestay (220) having an unfolded position and a folded position. A telescopic actuator (250) is coupled between the main strut (210) and the sidestay (220), so that when the actuator (250) has a first length the sidestay (220) locks the main strut (210) in the extended position, and when the actuator (250) has a second length the sidestay (220) is in the folded position and the main strut (210) is in the retracted position.

94. 发明授权

EP3744632B1 ELECTRICALLY POWERED DOWNLOCK ACTUATION SYSTEM 有权
公开(公告)号：EP3744632B1
公开(公告)日：2023-12-06
申请号：EP20187236.3
申请日：2017-07-27
发明人： DITZLER, Adam J.
IPC分类号： B64C25/20 , B64C25/26

95. 发明公开

EP4234400A1 ELECTROMECHANICAL ACTUATOR PUMP 审中-实审
公开(公告)号：EP4234400A1
公开(公告)日：2023-08-30
申请号：EP23172597.9
申请日：2020-11-09
申请人： Goodrich Corporation
发明人： ALLEN, Jason Bradley
IPC分类号： B64C25/50 , B64C25/24 , B64C25/22 , F16D25/00 , F16D48/02 , B64C25/26 , B64C25/16 , H02K7/108
摘要： A nose landing gear system, comprising: an electric motor (440); a hydraulic pump (450) connected to the electric motor; a gearbox (442) connected to the electric motor; and a clutch (444) configured to mechanically couple the gearbox to a steering collar (415); and further comprising a clutch control valve (441) configured to engage and disengage the clutch.

96. 发明授权

EP3498600B1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
公开(公告)号：EP3498600B1
公开(公告)日：2023-08-09
申请号：EP17208258.8
申请日：2017-12-18
发明人： PRICE, Neil Richard
IPC分类号： B64C25/22 , B64C25/26 , B64C25/10 , F16F13/00 , F16F1/02

97. 发明公开

EP4219298A1 SYSTEM AND METHOD FOR LANDING GEAR RETRACTION 审中-实审
公开(公告)号：EP4219298A1
公开(公告)日：2023-08-02
申请号：EP23174148.9
申请日：2020-03-26
申请人： Airbus Operations Limited
发明人： L'ALLIER, Paul Gordon
IPC分类号： B64C25/18 , B64C25/20 , B64C25/22 , B64C25/26
摘要： A retractable landing gear on an aircraft is operated by a landing gear control system 20 having a manually operable lever 26 movable from a first, e.g. gear-down, position to a second, e.g. gear-up position, in response to which a signal (e.g. a gear-up command) is outputted causing the landing gear to move to an up position. The landing gear control system 20 also includes a motor 40 configured to move the lever 26 in dependence on a signal, for example a signal received by a landing gear lever control unit 42 from a take-off detection system 46 which indicates that the aircraft has taken-off. Thus, the lever 26 may be considered as being configured both to be operated by a pilot of the aircraft manually and to be operated by the motor automatically.

98. 发明公开

EP4168309A1 DISPOSITIF DE VERROUILLAGE D'ATTERRISSEUR 审中-实审
公开(公告)号：EP4168309A1
公开(公告)日：2023-04-26
申请号：EP21734133.8
申请日：2021-06-21
申请人： Safran Landing Systems
发明人： DUBOIS, Sébastien , DOUX, Aurélien , HENRION, Philippe , PAVOINE, Vincent
IPC分类号： B64C25/22 , B64C25/26

99. 发明授权

EP3805097B1 ELECTRICALLY OPERATED LANDING GEAR LOCK SYSTEM 有权
公开(公告)号：EP3805097B1
公开(公告)日：2023-04-12
申请号：EP19215653.7
申请日：2019-12-12
发明人： KULKARNI, Sagar , VASUDEVA, Vishwanath , MARAPPAN, Bharath
IPC分类号： B64C25/26 , B64C25/30 , B64C25/28

100. 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.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式