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    LANDING GEAR WITH STEERABLE AXLE
    1.
    发明申请
    LANDING GEAR WITH STEERABLE AXLE 审中-公开
    具有可转向轴的接地齿轮

    公开(公告)号：WO2011098745A3

    公开(公告)日：2013-05-02

    申请号：PCT/GB2010000244

    申请日：2010-02-10

    Applicant: MESSIER DOWTY LTD ,  BENNETT IAN ,  MENEZES ROBERT ,  SHAW PAUL

    Inventor： BENNETT IAN ,  MENEZES ROBERT ,  SHAW PAUL

    IPC: B64C25/34 ,  B64C25/48 ,  B64C25/50 ,  F15B15/26

    CPC classification number: B64C25/34 ,  B64C25/48 ,  B64C25/50 ,  B64C2025/345

    Abstract: There is described a landing gear having a bogie including a elongated beam (2) for accommodating at least two axles receiving each a pair of ground engaging wheels, at least one axle (5) being pivotally mounted on the elongated beam. The landing gear further includes axle travel limitation means (10) extending between said pivotable axle and said elongated beam to be hitched up thereto, said travel limitation means being deformable one way starting from an stable and lockable state thereof corresponding to a landing position of said pivotable axle. There are also described independently lockable and actuatable telescopic struts.

    Abstract translation: 描述了一种具有转向架的起落架，该转向架包括用于容纳至少两个接收每一个地面接合轮的轴的细长梁（2），至少一个轴（5）可枢转地安装在细长梁上。 起落架还包括在所述可枢转轴与所述细长梁之间延伸的轴行进限制装置（10），所述轴行程限制装置（10）在与之相连的所述细长梁之间延伸，所述行驶限制装置可自其稳定和可锁定的状态单向变形， 可枢转轴。 还描述了独立的可锁定和可致动的伸缩支柱。

    LANDING GEAR
    4.
    发明申请
    LANDING GEAR 审中-公开
    起落架

    公开(公告)号：WO2011089426A1

    公开(公告)日：2011-07-28

    申请号：PCT/GB2011/050086

    申请日：2011-01-19

    Applicant: MESSIER-DOWTY LIMITED ,  BENNETT, Ian

    Inventor： BENNETT, Ian

    IPC: B64C25/50

    CPC classification number: B64C25/34 ,  B64C2025/345

    Abstract: A landing gear (70) for an aircraft, the landing gear including an axle (14) pivotally connected to a bogie beam (12) and a locking device (11c), the locking device being arranged to couple the axle to the bogie beam, the locking device including a movable member and a follower (22), the movable member (60) being arranged to be moved by an actuator between first and second configurations, the locking device being arranged such that movement of the movable member towards the second configuration causes corresponding movement of the follower so as to transfer a steering force to the axle through the follower which causes the axle to rotate in a first direction, wherein, with the movable member in the first configuration, the locking device is arranged with the follower in a first configuration that inhibits the movable member being moved by an external force applied to the axle and, with the movable member in the second configuration, the locking device is arranged with the follower in a second configuration that permits the movable member to be moved by an external force applied to the axle.

    Abstract translation: 一种用于飞行器的起落架（70），起落架包括枢转地连接到转向架梁（12）和锁定装置（11c）的轴（14），该锁定装置被布置成将车轴连接到转向架梁， 所述锁定装置包括可动构件和从动件（22），所述可动构件（60）被布置成在第一和第二构造之间由致动器移动，所述锁定装置被布置成使得所述可动构件朝向所述第二构造 导致从动件的相应运动，以便通过随动件将转向力传递到轴，该随动件使轴沿第一方向旋转，其中，在第一构造中的可动构件中，锁定装置与随动件一起布置 第一构造，其通过施加到所述轴的外力来抑制所述可动构件的移动，并且在所述可动构件处于所述第二构造的情况下，所述锁定装置与所述随动件一起布置成 允许可动构件通过施加到车轴的外力而移动的第二构造。

    MAIN LANDING GEAR WITH RIGID REAR STAY
    5.
    发明申请
    MAIN LANDING GEAR WITH RIGID REAR STAY 审中-公开

    公开(公告)号：WO2011023980A3

    公开(公告)日：2011-03-03

    申请号：PCT/GB2010/051351

    申请日：2010-08-16

    Applicant: MESSIER-DOWTY LIMITED ,  BENNETT, Ian

    Inventor： BENNETT, Ian

    IPC: B64C25/12 ,  B64C25/34

    Abstract: A main landing gear assembly for an aircraft comprising: an elongate beam pivotally coupled about its longitudinal axis to the aircraft such that the axis of rotation of the elongate beam is generally parallel to the longitudinal axis of the aircraft fuselage; a shock strut pivotally coupled at a first end to the elongate beam and coupled at a second end to a wheel assembly; a folding forward stay pivotally coupled at a first end to the elongate beam and pivotally coupled at a second end to the shock strut; and a rigid rear stay pivotally coupled at a first end to the aircraft and pivotally coupled at a second end to the shock strut, the rigid rear stay being arranged to restrain the path of the shock strut when moving between a deployed and a retracted position such that the wheel assembly is located forward and inboard in the retracted position in comparison with its location in the deployed position.

    LOAD DETECTION IN AN AIRCRAFT LANDING GEAR
    6.
    发明申请
    LOAD DETECTION IN AN AIRCRAFT LANDING GEAR 审中-公开
    飞机起落架载荷检测

    公开(公告)号：WO2009047367A2

    公开(公告)日：2009-04-16

    申请号：PCT/EP2008/063743

    申请日：2008-10-13

    Applicant: MESSIER-DOWTY LIMITED ,  BENNETT, Ian

    Inventor： BENNETT, Ian

    IPC: B64C25/00

    CPC classification number: B64C25/34 ,  B64C25/58 ,  B64D2045/008 ,  F16F9/3264

    Abstract: A landing gear for an aircraft comprises: a shock absorber strut (1) with upper and lower telescoping portions (2, 3), the upper portion (2) being connectable to the airframe of the aircraft; an arm (4) to extend fore and aft relative to the aircraft and carrying a landing wheel, (7, 7 1 ), and pivotally connected by a main pivot (5) to the lower portion (3) of the shock absorber strut; and a load reacting unit (9) connected between the arm (4) and the shock absorber strut (1) for reacting to load applied between the arm and shock absorber strut on landing, and an indicator (60) for monitoring the load applied to the load reacting unit (9) on landing. The load reacting unit (9) may be connected between a forward end of the arm (4) and the upper portion (2) of the shock absorber strut to make the gear act as a semi-levered landing gear. Alternatively, the load reacting unit (9) may be connected between the arm (4) and the lower portion (3) of the shock absorber strut to act as a pitch trimmer. The arm (4) may comprise a bogie beam with fore and aft landing wheels (7, 7 1 ) with the main pivot (5) therebetween. The load reacting unit (9) preferably comprises a fluid pressure unit and the indicator (60) comprises a mechanical indicator that operates at a predetermined pressure threshold.

    Abstract translation: 用于飞机的起落架包括：具有上和下伸缩部分（2,3）的减震器支柱（1），上部部分（2）可连接到飞行器的机身; 臂（4），其相对于飞行器前后延伸并承载着陆车轮（7,71），并且通过主枢轴（5）枢转地连接到减震器支柱的下部（3）; 以及连接在所述臂（4）和所述减震器支柱（1）之间的负载反作用单元（9），用于响应于在着陆时施加在所述臂和减震器支柱之间的负载;以及指示器（60），用于监视施加到 负载反应单元（9）着陆。 负载反应单元（9）可以连接在臂（4）的前端和减震器支柱的上部（2）之间，以使齿轮作为半起落架起落架。 或者，负载反应单元（9）可以连接在臂（4）和减震器支柱的下部（3）之间，用作俯仰修剪器。 臂（4）可以包括具有前和后着陆轮（7,71）的转向架梁，其中主枢轴（5）在其间。 负载反应单元（9）优选地包括流体压力单元，并且指示器（60）包括在预定压力阈值下操作的机械指示器。

    METHODS AND SYSTEMS FOR LATERALLY STABILIZED CONSTRAINT OF SPINOUS PROCESSES
    7.
    发明申请
    METHODS AND SYSTEMS FOR LATERALLY STABILIZED CONSTRAINT OF SPINOUS PROCESSES 审中-公开
    旋转过程的侧向稳定约束的方法和系统

    公开(公告)号：WO2008051806A3

    公开(公告)日：2008-07-24

    申请号：PCT/US2007081835

    申请日：2007-10-18

    Applicant: SIMPIRICA SPINE INC ,  ALAMIN TODD ,  BENNETT IAN ,  CAHILL COLIN ,  FIELDING LOUIS

    Inventor： ALAMIN TODD ,  BENNETT IAN ,  CAHILL COLIN ,  FIELDING LOUIS

    IPC: A61F5/02

    CPC classification number: A61B17/7065 ,  A61B17/7055 ,  A61B17/7062 ,  A61B17/842

    Abstract: A spinal implant for limiting flexion of the spine includes a tether structure for encircling adjacent spinal processes. Usually, a pair of compliance members will be provided as part of the tether structure for elastically limiting flexion while permitting an extension. A cross-member is provided between the compliance member or other portions of the tether structure to stabilize the tether structure and prevent misalignment after implantation.

    Abstract translation: 用于限制脊柱弯曲的脊柱植入物包括用于环绕相邻脊柱过程的系绳结构。 通常，将提供一对顺应性构件作为系绳结构的一部分，用于弹性限制弯曲，同时允许延伸。 在连接构件或系链结构的其它部分之间设置横向构件以稳定系绳结构并防止植入后的未对准。

    PIN JOINT ASSEMBLY
    9.
    发明申请
    PIN JOINT ASSEMBLY 审中-公开
    PIN接头总成

    公开(公告)号：WO2013011324A1

    公开(公告)日：2013-01-24

    申请号：PCT/GB2012/051736

    申请日：2012-07-20

    Applicant: MESSIER-DOWTY LIMITED ,  GREEN, Chris ,  BENNETT, Ian

    Inventor： GREEN, Chris ,  BENNETT, Ian

    IPC: F16C11/04 ,  F16C25/04

    CPC classification number: F16C11/045 ,  F16C25/04 ,  F16C2326/43

    Abstract: A pin joint assembly for an aircraft landing gear comprising: an elongate joint pin (206); at least one first lug (202a, 202) through which the joint pin passes; and at least one second lug (204) through which the joint pin passes; wherein the joint pin includes first (212) and second (212a) retaining elements located at opposite ends of the joint pin and arranged to maintain the location of the joint pin relative to the first and second lugs, and wherein the pin joint assembly further comprises a respective resilient member (214, 214a) located between each of the retaining elements and a respective one of the first and second lugs, each resilient element being elastically deformable.

    Abstract translation: 一种用于飞机起落架的销接头组件，包括：细长接头销（206）; 至少一个第一凸耳（202a，202），所述接头销通过所述第一凸耳; 和至少一个第二凸耳（204），所述接头销通过所述第二凸耳（204）; 其中所述接合销包括位于所述接头销的相对端处的第一（212）和第二（212a）保持元件，并且被布置成保持所述接头销相对于所述第一和第二接头的位置，并且其中所述销接头组件还包括 位于每个保持元件之间的相应的弹性构件（214,214a）和第一和第二凸耳中的相应的一个，每个弹性元件可弹性变形。

    LANDING GEAR COMPRISING HYDRAULIC FLUID REPLENISHMENT DEVICE
    10.
    发明申请
    LANDING GEAR COMPRISING HYDRAULIC FLUID REPLENISHMENT DEVICE 审中-公开
    包括液压流体补偿装置的接地齿轮

    公开(公告)号：WO2012101422A1

    公开(公告)日：2012-08-02

    申请号：PCT/GB2012/050079

    申请日：2012-01-16

    Applicant: MESSIER-DOWTY LIMITED ,  BACON, Richard ,  LAWSON, Steven ,  BENNETT, Ian

    Inventor： BACON, Richard ,  LAWSON, Steven ,  BENNETT, Ian

    IPC: B64C25/60

    CPC classification number: B64C25/60

    Abstract: An aircraft landing gear including a shock absorber and a fluid replenishment device, the shock absorber having a compression chamber containing hydraulic fluid and the fluid replenishment device including a recuperator chamber for providing hydraulic fluid to the compression chamber of the shock absorber, the recuperator chamber including: a closed container defining an internal space and having: a first port coupled in a fluid tight manner to the compression chamber of the shock absorber; a second port arranged to be coupled in a fluid tight manner to a pressurised source of auxiliary hydraulic fluid; and a third port arranged to be coupled in a fluid tight manner to a second source of pressurised fluid; a movable element movably mounted within the container and arranged to divide the internal space into first and second subspaces, the first and second ports being in fluid communication with the first subspace and the third port being in fluid communication with the second subspace; and a valve having a open configuration in which the auxiliary hydraulic fluid may pass into the first subspace and a closed configuration wherein the second port is sealed in a fluid tight manner, wherein the fluid replenishment device is arranged such that, when the pressure of fluid within the second subspace is greater than the pressure of fluid within the first subspace, the movable element moves towards the valve such that it can mechanically couple with the valve so as to open the valve.

    Abstract translation: 一种包括减震器和流体补给装置的飞机起落架，所述减振器具有包含液压流体的压缩室，所述流体补给装置包括用于向减震器的压缩室提供液压流体的换热器室，所述换热器室包括 ：限定内部空间的密封容器，具有：以流体密封的方式连接到减震器的压缩室的第一端口; 第二端口，其布置成以流体密封的方式联接到辅助液压流体的加压源; 以及第三端口，其布置成以流体密封的方式联接到第二加压流体源; 活动元件，其可移动地安装在所述容器内并被布置成将所述内部空间分成第一和第二子空间，所述第一和第二端口与所述第一子空间流体连通，所述第三端口与所述第二子空间流体连通; 以及具有打开构造的阀，其中所述辅助液压流体可以进入所述第一子空间，并且闭合构造，其中所述第二端口以流体密封的方式被密封，其中所述流体补充装置被布置成使得当流体的压力 在第二子空间内的流体的压力大于第一子空间内的流体压力，可移动元件朝向阀移动，使得其可以与阀机械地联接以打开阀。

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