公开(公告)号：WO2007015104A1

公开(公告)日：2007-02-08

申请号：PCT/GB2006/002918

申请日：2006-08-04

Applicant: MESSIER-DOWTY LIMITED ,  BENNETT, Ian ,  LANG, Richard, Charles ,  MENEZES, Robert, Anthony

Inventor： BENNETT, Ian ,  LANG, Richard, Charles ,  MENEZES, Robert, Anthony

IPC: B64C25/00

CPC classification number: B64C25/60 ,  B64C25/22 ,  B64C25/34 ,  B64C25/58

Abstract: A semi-levered landing gear for an aircraft comprises a main shock absorber strut (1) connected to the airframe; a bogie beam (4) extending fore and aft of the airframe with forward and aft wheels (J, T) and a main pivot connection (5) to the strut (1) between the forward and aft wheels (7, T) and an auxiliary actuator (49) connected between the strut (1) and the front of the bogie beam (4) at an auxiliary pivot (14). The auxiliary actuator (49) comprises a two stage telescopic hydraulic unit comprising a first stage piston and cylinder actuator (59, 63) and a second stage piston and cylinder actuator (56, 50) operating coaxially within an outer casing (50). A respective piston rod (65, 60) each extends from each end of the casing (50) and is connected to a respective one of said (strut 1) and bogie beam (4). The first stage actuator (59, 63) is operable to an extended position, and the second stage actuator (56, 60) is operable between a retracted position (Fig. 11) and an extended position (Fig. 12) defined by respective end stops (75, 77) within the outer casing (50) and serves to control the tilt position of the bogie beam (4) relative to the strut (1). The second stage actuator (56, 60), when in the retracted position with the first stage actuator (59, 63) in the extended position, limits the length of the auxiliary actuator (9) between its connections (62, 67) to the strut (1) and bogie beam (4), so as to assume a predetermined intermediate length in which the bogie beam (4) is restrained to tilt about the auxiliary pivot (14) and thereby lengthens the landing gear during take-off. The second stage actuator (56, 60), when in the extended position with the first stage actuator (59, 63) in the extended position, allows the length of the auxiliary actuator (49) to assume a predetermined maximum length in which the bogie beam (4) is tilted about the main pivot (5) to a stowing position for stowing the landing gear in the aircraft.

Abstract translation: 用于飞机的半起落架起落架包括连接到机身的主减震器支柱（1）; 在前后轮（7，T）和后轮（7，T）之间的支撑件（1）的前后轮（J，T）和主枢轴连接件（5）的前部和后部延伸的转向架梁（4） 辅助致动器（49）在辅助枢轴（14）处连接在支柱（1）和转向架​​梁（4）的前部之间。 辅助致动器（49）包括两级伸缩液压单元，其包括第一级活塞和气缸致动器（59,63）和在外壳（50）内同轴工作的第二级活塞和气缸致动器（56,50）。 相应的活塞杆（65,60）各自从壳体（50）的每个端部延伸并且连接到所述（支柱1）和转向架​​梁（4）中的相应一个。 第一级致动器（59,63）可操作到延伸位置，并且第二级致动器（56,60）可在缩回位置（图11）和由相应端限定的延伸位置（图12）之间操作 在外壳（50）内的止挡（75,77），并用于控制转向架（4）相对于支柱（1）的倾斜位置。 第二级致动器（56,60）当处于处于伸出位置的第一级致动器（59,63）的缩回位置时，将辅助致动器（9）在其连接件（62,67）之间的长度限制到 支柱（1）和转向架​​梁（4），以便呈现预定的中间长度，其中转向架梁（4）被限制在辅助枢轴（14）周围倾斜，从而在起飞期间延长起落架。 第二级致动器（56,60）当处于处于延伸位置的第一级致动器（59,63）的延伸位置时，允许辅助致动器（49）的长度呈现预定的最大长度，其中转向架 梁（4）围绕主枢轴（5）倾斜到收起位置，用于收起飞机上的起落架。

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。

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。

公开(公告)号：WO2012059742A1

公开(公告)日：2012-05-10

申请号：PCT/GB2011/052108

申请日：2011-10-28

Applicant: MESSIER-DOWTY LIMITED ,  BENNETT, Ian ,  SEXTON, Matthew

Inventor： BENNETT, Ian ,  SEXTON, Matthew

IPC: B64C25/00 ,  B64C25/34

CPC classification number: B64C25/001 ,  B64C25/34

Abstract: An aircraft landing gear assembly comprising a bogie beam (2), an axle (4) extending through the bogie beam and a jacking dome fitting (6) extending through a sidewall (8) of the bogie beam and arranged to transfer vertical loads applied to the jacking dome fitting to the axle.

Abstract translation: 一种飞机起落架组件，包括转向架梁（2），延伸穿过转向架梁的轴（4）和延伸穿过转向架梁的侧壁（8）的顶起的圆顶配件（6），并布置成传递施加到 起落架的圆顶装配到轴上。

公开(公告)号：WO2010125365A1

公开(公告)日：2010-11-04

申请号：PCT/GB2010/050509

申请日：2010-03-25

Applicant: MESSIER-DOWTY LIMITED ,  BENNETT, Ian

Inventor： BENNETT, Ian

IPC: F16F9/36

CPC classification number: F16F9/367 ,  F16C29/001

Abstract: A bearing assembly (2') comprising a housing (3') supporting first and second bearing ring portions (4, 4') with bearing surfaces to engage an inner tubular member (1') at axially spaced regions, characterised in that either: said bearing ring portions are provided by separate bearing rings (4') supported in the housing member (3') with bearing surfaces of different diameters; or said bearing ring portions are provided by a single bearing ring (4'') that is free to flex radially and is supported so that the second bearing ring portion is free to flex radially under load and its bearing surface than assumes a position with a greater diameter than that of the first bearing ring portion (4'').

Abstract translation: 一种轴承组件（2'），其包括支撑具有轴承表面的第一和第二轴承环部分（4,4'）的壳体（3'），以在轴向间隔开的区域处接合内部管状构件（1'），其特征在于： 所述轴承环部分由支撑在壳体构件（3'）中的不同直径的轴承表面的分离的轴承环（4'）提供; 或所述轴承环部分由单个轴承环（4“）提供，所述单个轴承环（4”）可径向自由地弯曲并且被支撑，使得第二轴承环部分在负载下径向自由地弯曲并且其轴承表面比假定具有 比第一轴承环部分（4“）的直径大。

公开(公告)号：WO2009037465A1

公开(公告)日：2009-03-26

申请号：PCT/GB2008/003175

申请日：2008-09-19

Applicant: MESSIER-DOWTY LIMITED ,  BENNETT, Ian

Inventor： BENNETT, Ian

IPC: B64C25/00 ,  B64F5/00

CPC classification number: B64C25/00 ,  B64D2045/008 ,  B64F5/60 ,  F16C11/045 ,  F16C17/24 ,  F16C2326/43 ,  G01L5/0071

Abstract: An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is contacted and loaded by the first load bearing member (10) when it is loaded beyond a load limit. Preferably, the first load bearing member (10) has a yield point below the load limit and takes a permanent set once the yield point has been exceeded. A lateral probe (18) cooperates with the first load bearing member as it moves towards the second load bearing member and in turn deflects an indicator member (20) which takes a permanent set when a yield point is exceeded. Ready inspection of the indicator member then reveals whether or not it has been bent.

Abstract translation: 过载检测组件包括适于响应待监测的负载而侧向弯曲的第一承载构件（10），与第一正常负载条件间隔开的第二承载构件（11），其与第一负载承载构件 当第一承载构件（10）被加载超过负载极限时。 优选地，第一承载构件（10）具有低于载荷极限的屈服点，并且一旦超过屈服点就采用永久变形。 横向探头（18）在第一承载构件向第二承载构件移动时与第一承载构件协作，并且当超过屈服点时，使指示器构件（20）偏转，该指示构件（20）是永久变形的。 然后，对指示器构件进行准备检查，然后揭示其是否弯曲。

公开(公告)号：WO2011048394A1

公开(公告)日：2011-04-28

申请号：PCT/GB2010/050716

申请日：2010-04-30

Applicant: MESSIER-DOWTY LIMITED ,  HILLIARD, Matthew ,  BENNETT, Ian

Inventor： HILLIARD, Matthew ,  BENNETT, Ian

IPC: B64C25/34

CPC classification number: B64C25/34

Abstract: An aircraft landing gear assembly including a bogie beam, a landing gear strut (1) having a first end arranged to be pivotally coupled to an aircraft and a second end pivotally coupled to the bogie beam (3), and a stop (13) arranged to limit pivotal movement of the bogie beam relative to the landing gear strut, wherein the stop comprises at least one elongate member arranged to be deflectable in bending when the bogie beam reaches a pivotal limit.

Abstract translation: 包括转向架梁的飞机起落架组件，具有被布置成可枢转地联接到飞行器的第一端的起落架支柱（1）和枢转地联接到转向架梁（3）的第二端以及设置在所述转向架梁 以限制转向架相对于起落架支柱的枢转运动，其中止挡包括布置成当转向架梁达到枢转极限时可弯曲弯曲的至少一个细长构件。

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。

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.

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。