专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

31. 发明申请

WO2013079951A1 HEAT-TREATMENT METHOD AND APPARATUS 审中-公开
标题翻译：热处理方法和装置
公开(公告)号：WO2013079951A1
公开(公告)日：2013-06-06
申请号：PCT/GB2012/052954
申请日：2012-11-30
申请人： MESSIER-DOWTY LIMITED
发明人： SCHMIDT, Kyle , FORTIN, Rejean
IPC分类号： F27D3/00 , F27D5/00
CPC分类号： F27D3/0024 , F27D5/0006 , F27D5/0056
摘要： An apparatus for supporting one or more metal components during heat treatment comprising: a support platform; an elongate member extending from the support platform and removably attached to the support platform; and a locking mechanism which locks the elongate member to the platform, wherein the locking mechanism comprises a plurality of engagement portions pivotally mounted at a first end of the elongate member and arranged to engage with the interior of a bore in the support platform.
摘要翻译：一种用于在热处理期间支撑一个或多个金属部件的装置，包括：支撑平台; 细长构件，其从所述支撑平台延伸并可移除地附接到所述支撑平台; 以及锁定机构，其将所述细长构件锁定到所述平台，其中所述锁定机构包括枢转地安装在所述细长构件的第一端处并且布置成与所述支撑平台中的孔的内部接合的多个接合部分。

32. 发明申请

WO2013005032A1 PROFILED BEARING 审中-公开
标题翻译：轮廓轴承
公开(公告)号：WO2013005032A1
公开(公告)日：2013-01-10
申请号：PCT/GB2012/051560
申请日：2012-07-04
申请人： MESSIER-DOWTY LIMITED , GOSSAGE, Gary , MICHAELIDES, Peter , VATOVEC, Andraz
发明人： GOSSAGE, Gary , MICHAELIDES, Peter , VATOVEC, Andraz
IPC分类号： F16C23/04 , F16C23/08
CPC分类号： F16C23/041 , F16C23/08
摘要： A bearing (10) arranged to receive a shaft (8) therein, the bearing including a contact surface (12) having a curved surface profile, the surface profile being arranged to conform to the curvature of the shaft (8) when the shaft is subject to a predetermined load.
摘要翻译：一种轴承（10），其布置成在其中容纳轴（8），所述轴承包括具有弯曲表面轮廓的接触表面（12），所述表面轮廓被布置成当所述轴是轴时，与所述轴（8）的曲率一致受到预定的负载。

33. 发明申请

WO2012136978A1 AN AIRCRAFT LANDING GEAR 审中-公开
标题翻译：飞机起落架
公开(公告)号：WO2012136978A1
公开(公告)日：2012-10-11
申请号：PCT/GB2012/050622
申请日：2012-03-22
申请人： MESSIER-DOWTY LIMITED , LACY, Stuart , CUMNER, Geoff
发明人： LACY, Stuart , CUMNER, Geoff
IPC分类号： B64C25/00
CPC分类号： B64C25/001 , B64C2025/003
摘要： An aircraft landing gear (10) comprising a noise-inducing component region (12) and an airflow disruption element (16) having a first configuration in which it is spaced from, and arranged in an upstream relationship with respect to, the noise-inducing component region such that, in use with the landing gear deployed, the airflow disruption element faces, and at least partially disrupts, an airflow(A) moving towards the noise-inducing component region, wherein the cross-sectional area of the airflow disruption element is less than the cross-sectional area of the noise-inducing component region.
摘要翻译：一种飞机起落架（10），包括噪声诱导组件区域（12）和气流破坏元件（16），其具有第一配置，其中它与噪声诱导分配区域，使得在使用起落架部署时，气流破坏元件面向并且至少部分地中断朝向噪声诱导部件区域移动的气流（A），其中气流破坏元件的横截面积小于噪声诱导分量区域的横截面面积。

34. 发明申请

WO2012069806A1 MECHANICAL POSITION INDICATOR FOR UN AIRCRAFT LANDING GEAR 审中-公开
标题翻译：联合国飞机起落架机械位置指示器
公开(公告)号：WO2012069806A1
公开(公告)日：2012-05-31
申请号：PCT/GB2011/052182
申请日：2011-11-09
申请人： MESSIER-DOWTY LIMITED , HODGKINSON, Ben , LACY, Stuart , WEBB, Chris , ANSON, Garry
发明人： HODGKINSON, Ben , LACY, Stuart , WEBB, Chris , ANSON, Garry
IPC分类号： B64D45/00 , B64C25/00
CPC分类号： B64D45/0005 , B64C25/00 , B64D2045/008
摘要： A mechanical position indicator (9a) for providing a visual indication that a first part of an aircraft landing gear (1) has assumed a predetermined position relative to a second part, the position indicator (9a) being arranged to be coupled to a first one of the first and second parts and in a first state arranged to hold an indicator element (15a) in a deployed position, the position indicator (9a) being arranged such that upon the first part assuming the predetermined position relative to the second part, a second one of the first and second parts changes the position indicator (9a) from the first state to a second state in which the indicator element (15a) is displaced from the deployed position, the position indicator (9a) being arranged to inhibit the indicator element (15a) thereafter returning to the deployed position.
摘要翻译：一种用于提供飞行器起落架（1）的第一部分相对于第二部分已经具有预定位置的视觉指示的机械位置指示器（9a），所述位置指示器（9a）被布置成联接到第一部分的第一和第二部分，并且在布置成将展示元件（15a）保持在展开位置的第一状态下，位置指示器（9a）被布置成使得在第一部分相对于第二部分呈现预定位置时，第一和第二部分中的第二部分将位置指示器（9a）从第一状态改变到指示元件（15a）从展开位置移位的第二状态，位置指示器（9a）布置成禁止指示器元件（15a）此后返回到展开位置。

35. 发明申请

WO2007015104A1 LANDING GEAR 审中-公开
标题翻译：起落架
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
申请人： MESSIER-DOWTY LIMITED , BENNETT, Ian , LANG, Richard, Charles , MENEZES, Robert, Anthony
发明人： BENNETT, Ian , LANG, Richard, Charles , MENEZES, Robert, Anthony
IPC分类号： B64C25/00
CPC分类号： B64C25/60 , B64C25/22 , B64C25/34 , B64C25/58
摘要： 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.
摘要翻译：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。

36. 发明申请

WO2006010890A1 AIRCRAFT LANDING GEAR 审中-公开
标题翻译：飞机起落架
公开(公告)号：WO2006010890A1
公开(公告)日：2006-02-02
申请号：PCT/GB2005/002815
申请日：2005-07-18
申请人： MESSIER-DOWTY LIMITED , THULBON, Jonathan
发明人： THULBON, Jonathan
IPC分类号： B64C25/50
CPC分类号： B64C25/50 , B64C25/14
摘要： Aircraft landing gear includes a retractable housing comprising an upper leg (11); a lower leg (15) including a wheel axle (16) slidingly disposed within the upper leg (11) and resiliently biassed to an extended condition; a turning collar (18) rotatably disposed about the housing and having connection means for a drag stay (17); and a steering collar (19) operatively connected to a steering motor (41) and connected to the lower leg (15) by a torque link (21, 22); in which the turning collar (18) is provided with a cam surface (24) which cooperates in use with the torque link (21, 22) to maintain the lower leg (15) with the wheel in the fore-and-aft position when in the extended condition.
摘要翻译：飞机起落架包括包括上腿（11）的可伸缩壳体; 包括滑动地布置在所述上腿部（11）内并弹性偏压到延伸状态的轮轴（16）的小腿（15）旋转轴环（18），其可旋转地设置在所述壳体周围并具有用于拖曳撑杆（17）的连接装置; 以及操作性地连接到转向马达（41）并通过扭矩连杆（21,22）连接到所述小腿（15）的转向轴环（19）; 其中所述转动套环（18）设置有凸轮表面（24），所述凸轮表面与所述扭矩连杆（21,22）配合使用以将所述小腿（15）与所述车轮保持在所述前后位置，在延长的条件。

37. 发明授权

US09562584B2 Aircraft landing gear fluid gauge 有权
标题翻译：飞机起落架流量计
公开(公告)号：US09562584B2
公开(公告)日：2017-02-07
申请号：US14357071
申请日：2012-11-01
申请人： Messier-Dowty Limited
发明人： Kyle Schmidt
IPC分类号： F16F9/32 , B64C25/60 , F16F9/06
CPC分类号： F16F9/3264 , B64C25/60 , F16F9/06
摘要： An oleo-pneumatic shock absorber having a casing, a rod slidably mounted in the casing, first and second fluids in the casing, and a gauge. The gauge has a substrate positioned on the shock absorber. The substrate has a first region with a slot sized to fit an ultrasonic transducer arranged to encompass a range of possible oil levels within the shock absorber, a second region corresponding to a range of possible extension states of the shock absorber and a third region comprising one or more traces. Each trace corresponds to a temperature value and is indicative of an optimum relationship between the oil levels and the range of extension states at the respective temperature value associated with the trace.
摘要翻译：具有壳体的油气动减震器，可滑动地安装在壳体中的杆，壳体中的第一和第二流体以及量规。仪表具有位于减震器上的基板。衬底具有第一区域，其具有尺寸设计成适合布置成包围减震器内的可能油位范围的超声换能器的第一区域，对应于减震器的可能延伸状态的范围的第二区域和包括一个或更多痕迹。每个迹线对应于温度值，并且指示在与痕量相关联的相应温度值下油位与扩展状态的范围之间的最佳关系。

38. 发明申请

US20160375993A1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
标题翻译：飞机接地齿轮总成
公开(公告)号：US20160375993A1
公开(公告)日：2016-12-29
申请号：US15156820
申请日：2016-05-17
申请人： Messier-Dowty Limited
发明人： Robert Kyle Schmidt
IPC分类号： B64C25/62 , F16F13/00 , B64C25/60 , B64C25/34 , B64C25/10
CPC分类号： B64C25/62 , B64C25/10 , B64C25/34 , B64C25/60 , F16F13/007 , F16F2226/04 , F16F2230/0023
摘要： An aircraft landing gear assembly includes a mechanical structural linkage having a shock absorber and a linkage abutment which are biased apart by a mechanical spring. The force required to deform the spring sufficiently to place the linkage abutment at a predefined distance with respect to the shock absorber abutment is less than the breakout force of the shock absorber.
摘要翻译：飞机起落架组件包括具有减震器和通过机械弹簧偏压分离的连杆支座的机械结构连杆。将弹簧充分变形以将连杆支座相对于减震器基座放置在预定距离所需的力小于减振器的突出力。

39. 发明申请

US20160272305A1 AIRCRAFT LANDING GEAR ASSEMBLY 有权
标题翻译：飞机接地齿轮总成
公开(公告)号：US20160272305A1
公开(公告)日：2016-09-22
申请号：US15072953
申请日：2016-03-17
申请人： Messier-Dowty Limited
发明人： Robert Kyle Schmidt
IPC分类号： B64C25/26 , B64C25/10
CPC分类号： B64C25/26 , B64C25/10 , B64C25/58
摘要： An aircraft landing gear assembly includes a fibre composite leaf spring arranged as a down lock spring to make the lock link.
摘要翻译：飞机起落架组件包括布置成下锁弹簧以制造锁定连杆的纤维复合板簧。

40. 发明申请

US20160052038A1 DEFORMATION APPARATUS (AS AMENDED) 有权
标题翻译：变形装置（如修改）
公开(公告)号：US20160052038A1
公开(公告)日：2016-02-25
申请号：US14780847
申请日：2014-03-10
申请人： MESSIER-DOWTY LIMITED
发明人： Jean-Philippe Villain-Chastre , Germain Forgeoux , Przemyslaw Grochola
IPC分类号： B21D26/033
CPC分类号： B21D26/033 , B21D22/16 , B21D31/06 , Y10T29/49805
摘要： Apparatus configured to deform a tubular work piece having a longitudinal axis, the apparatus comprising a support for supporting a tubular work piece to be deformed; rotation means for rotating the tubular work piece about its longitudinal axis; a nozzle for directing a stream of pressurised fluid at the tubular work piece in a direction transverse to the longitudinal axis of the tubular work piece; and means for moving one or both of the tubular work piece and the nozzle relative to one another such that the stream of pressurised fluid can be aimed at a plurality of locations along the tubular work piece; wherein the pressure of the fluid directed at the tubular work piece is great enough to cause deformation of the tubular work piece, but not so great that cutting of the tubular work piece can occur.
摘要翻译：用于使具有纵向轴线的管状工件变形的装置，该装置包括用于支撑待变形的管状工件的支撑件; 用于使管状工件围绕其纵向轴线旋转的旋转装置; 用于沿着与所述管状工件的纵向轴线横向的方向引导所述管状工件处的加压流体流的喷嘴; 以及用于相对于彼此移动管状工件和喷嘴中的一个或两个的装置，使得加压流体流可以瞄准沿着管状工件的多个位置; 其中指向管状工件的流体的压力足够大以引起管状工件的变形，但不会导致管状工件的切割发生。

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