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1. 发明申请

WO2013152300A2 MOTION CONTROLLED HELICOPTER AND ROTATION RATE SWITCHED FLUID LEAD LAG DAMPER 审中-公开
标题翻译：运动控制直升机和旋转速率切换流体导管拉杆阻尼器
公开(公告)号：WO2013152300A2
公开(公告)日：2013-10-10
申请号：PCT/US2013/035468
申请日：2013-04-05
申请人： LORD CORPORATION , FUHRER, Zachary , JOLLY, Mark , MARR, Conor
发明人： FUHRER, Zachary , JOLLY, Mark , MARR, Conor
IPC分类号： B64C27/51
CPC分类号： B64C27/51 , B64C27/32 , F16F9/064 , F16F9/20 , F16F9/504 , F16F13/08 , F16F2230/16
摘要： A method and centrifugal force switching dampers are disclosed for controlling helicopter ground resonance motions and air resonance motions. The helicopter lead-lag damper has a first ground resonance motion damping rate stage and a second air resonance motion damping rate stage. The damper includes a centrifugal force switch. The damper is oriented relative to the rotary wing rotation axis and helicopter blade. An in-flight rotation rate of the centrifugal force switching damper actuates the centrifugal force switch with the damper switching from the ground resonance motion damping rate stage to the second air resonance motion damping rate stage.
摘要翻译：公开了用于控制直升机地面共振运动和空气共振运动的方法和离心力切换阻尼器。直升机牵引滞后阻尼器具有第一接地共振运动阻尼速率级和第二空气谐振运动阻尼速率级。阻尼器包括离心力开关。阻尼器相对于旋转翼旋转轴和直升机叶片定向。离心力切换阻尼器的飞行中旋转速度致动离心力开关，其中阻尼器从地面共振运动阻尼速率级切换到第二空气共振运动阻尼速率级。

2. 发明申请

WO2012019117A3 FLUID ELASTOMERIC DAMPER ASSEMBLY INCLUDING INTERNAL PUMPING MECHANISM AND CONTROL VALVE 审中-公开
标题翻译：流体弹性阻尼器组件，包括内部泵送机构和控制阀
公开(公告)号：WO2012019117A3
公开(公告)日：2012-03-22
申请号：PCT/US2011046782
申请日：2011-08-05
申请人： LORD CORP , RUSSELL DONALD D
发明人： RUSSELL DONALD D
IPC分类号： B64C27/51
CPC分类号： B64C27/51 , F16F9/50 , F16F13/28 , F16K15/00 , Y10T137/7837
摘要： A rotary wing system with a rotating blade and a fluid damper with a damper fluid in a first variable volume chamber and a second variable volume chamber, with a fluid damping flow valve controlled conduit and a fluid flow pressure sensing control valve assembly between the first variable volume chamber and the second variable volume chamber. The fluid flow pressure sensing control valve assembly has a fluid flow pressure sensing control valve assembly control valve for obstructing a damper fluid flow through the fluid damping flow valve controlled conduit. A working of the first variable volume chamber and the second variable volume chamber by rotary wing motions actuates the opening of the fluid flow pressure sensing control valve assembly control valve that obstructs the damper fluid flow through the fluid damping flow valve controlled conduit.
摘要翻译：一种旋转翼系统，其具有旋转叶片和在第一可变容积腔室中具有阻尼流体的流体阻尼器和第二可变体积腔室，其中流体阻尼流量阀控制导管和流体流量压力感测控制阀组件位于第一变量容积室和第二可变容积室。流体流量压力感测控制阀组件具有流体流量压力感测控制阀组件控制阀，用于阻塞通过流体阻尼流量控制导管的阻尼器流体流动。第一可变体积腔室和第二可变体积腔室由旋转翼运动的作用致动流体流量压力感测控制阀组件控制阀的开口，阻塞流体通过流体阻尼流量控制导管的阻尼器流体流动。

3. 发明申请

WO2009079164A2 UNIFORM FATIGUE LIFE SPHERICAL ELASTOMERIC BEARING 审中-公开
标题翻译：均匀的疲劳寿命球状弹性轴承
公开(公告)号：WO2009079164A2
公开(公告)日：2009-06-25
申请号：PCT/US2008/084452
申请日：2008-11-23
申请人： SIKORSKY AIRCRAFT CORPORATION , CUNNINGHAM, Robert , BYRNES, Francis Edward
发明人： CUNNINGHAM, Robert , BYRNES, Francis Edward
IPC分类号： B64C27/35 , B64C27/48 , B64C27/51
CPC分类号： B64C27/35 , F16F1/40
摘要： An elastomeric spherical bearing includes a multiple of elastomeric layers with an essentially equivalent fatigue life.
摘要翻译：弹性体球轴承包括具有基本上相等的疲劳寿命的多个弹性层。

4. 发明申请

WO2007140362A9 ROTARY WING AIRCRAFT ROTARY LEAD LAG DAMPER 审中-公开
标题翻译：旋转翼飞机旋转导杆拉杆阻尼器
公开(公告)号：WO2007140362A9
公开(公告)日：2008-04-03
申请号：PCT/US2007069871
申请日：2007-05-29
申请人： LORD CORP , JONES PETER J , FUHRER ZACHARY
发明人： JONES PETER J , FUHRER ZACHARY
IPC分类号： B64C27/00 , B64C27/51
CPC分类号： B64C27/51 , F16F9/145
摘要： The invention provides a rotary damper (20) for controlling helicopter motions. The rotary damper includes an outer canister (22) with an inner paddle wheel receiving cavity (26) which receives an inner paddle wheel (60) with upper and lower elastomeric tubular intermediate members (78,80) between the inner paddle wheel and the outer canister. The canister and inner paddle wheel form neighboring variable volume chambers (82,84) in liquid communication through liquid damping conduits. A clockwise rotation of the inner paddle wheel about the center of rotation axis (28) relative to the outer canister pumps damper liquid from a second variable volume chamber through a first liquid conduit towards a first variable volume chamber, and a counterclockwise rotation of the paddle wheel relative to the outer canister pumps the damper liquid from the first variable volume chamber through the first liquid conduit towards the second variable volume chamber with the elastomeric tubular intermediate members providing for the relative rotation and containing the damper liquid in the damper.
摘要翻译：本发明提供一种用于控制直升机运动的旋转阻尼器（20）。旋转阻尼器包括具有内桨叶容纳腔（26）的外筒（22），其接纳内桨轮（60），所述内桨轮（60）具有在内桨叶轮和外桨轮之间的上和下弹性体管状中间构件（78,80）罐。罐和内桨轮形成通过液体阻尼管道液体连通的相邻的可变体积腔室（82,84）。内侧叶轮围绕旋转轴线（28）的中心相对于外部罐泵顺时针旋转，从第二可变容积室将液体通过第一液体导管朝向第一可变容积腔室缓冲液体，并且桨叶的逆时针旋转相对于外筒的车轮将来自第一可变容积室的阻尼液通过第一液体管道朝向第二可变容积室泵送，弹性体管状中间构件提供相对旋转并将阻尼液体容纳在阻尼器中。

5. 发明申请

WO2006086147A2 ASSEMBLY FOR PROVIDING FLEXURE TO BLADE SYSTEM 审中-公开
标题翻译：用于向刀片系统提供弯曲的组件
公开(公告)号：WO2006086147A2
公开(公告)日：2006-08-17
申请号：PCT/US2006/002413
申请日：2006-01-24
申请人： BELL HELICOPTER TEXTRON, INC. , STAMPS, Frank, B. , TISDALE, Patrick, R. , BRASWELL, James, L. , BASKIN, Charles, L., Jr. , CAMPBELL, Tom , LEDBETTER, Timothy, K. , ZIERER, Joseph, J. , REDDY, D., J. , WIINIKKA, Mark, A. , MARTIN, Ronnie, L. , HAYNIE, David, A. , SADLER, Stanley, Gene , MEASOM, Ron , OLDROYD, Paul , HIROS, Tricia , HARSE, Jim , MULLINS, Bob
发明人： STAMPS, Frank, B. , TISDALE, Patrick, R. , BRASWELL, James, L. , BASKIN, Charles, L., Jr. , CAMPBELL, Tom , LEDBETTER, Timothy, K. , ZIERER, Joseph, J. , REDDY, D., J. , WIINIKKA, Mark, A. , MARTIN, Ronnie, L. , HAYNIE, David, A. , SADLER, Stanley, Gene , MEASOM, Ron , OLDROYD, Paul , HIROS, Tricia , HARSE, Jim , MULLINS, Bob
IPC分类号： B64C27/33 , B64C27/51
CPC分类号： B64C27/48 , B64C27/33
摘要： An assembly for providing flexure to a blade of a rotary blade system, the assembly including an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces having a layer of cushioning material positioned thereon and secured thereto. The layer of cushioning material extending along and following the general contour of yoke surface, and the layer of cushioning material directly contacting a support plate. Another embodiment is an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle.
摘要翻译：一种用于向旋转叶片系统的叶片提供挠曲的组件，该组件包括具有上曲面的上支撑板，具有下弯曲表面的下支撑板和位于其间的轭。上和下磁轭表面中的至少一个具有定位在其上并固定到其上的缓冲材料层。缓冲材料层沿着轭铁表面的一般轮廓延伸并且沿着磁体表面的一般轮廓延伸，并且缓冲材料层直接接触支撑板。另一个实施例是用于向旋转刀片系统的刀片提供弯曲的组件，包括具有上曲面的上支撑板，具有下弯曲表面的下支撑板和位于其间的直接接触支撑板其中一个弯曲表面是不形成圆周的一部分的非圆弧。

6. 发明申请

WO2005049421A3 SOFT IN-PLANE ROTOR HUB 审中-公开
公开(公告)号：WO2005049421A3
公开(公告)日：2005-06-02
申请号：PCT/US2004/027990
申请日：2004-08-27
申请人： BELL HELICOPTER TEXTRON INC. , STAMPS, Frank, B. , SMITH, Michael, R. , BOTHWELL, Christopher, M. , CORSO, Lawrence, M. , BRASWELL, James, L., Jr. , POPELKA, David, A. , SCHELLHASE, Ernst, C. , HOLLIMON, Charles, L. , NEWMAN, Thomas, J. , BASKIN, Bryan , CAMPBELL, Thomas, C. , ROBERTSON, Daniel, B.
发明人： STAMPS, Frank, B. , SMITH, Michael, R. , BOTHWELL, Christopher, M. , CORSO, Lawrence, M. , BRASWELL, James, L., Jr. , POPELKA, David, A. , SCHELLHASE, Ernst, C. , HOLLIMON, Charles, L. , NEWMAN, Thomas, J. , BASKIN, Bryan , CAMPBELL, Thomas, C. , ROBERTSON, Daniel, B.
IPC分类号： B64C27/51
摘要： A rotor hub assembly for a rotary-wing aircraft has a central member and a plurality of blade grips adapted for attaching rotor blades to the central member. The blade grips are pivotally attached to the central member and are capable of pivoting about a pivot axis generally normal to a plane of rotation of the blades. The pivoting allows for in-plane motion of the blades relative to the central member. A damper is operably connected to each blade grip for damping the in-plane motion of the associated blade, each damper being selectively switchable between at least two spring rates.

7. 发明申请

WO2002085705A1 ROTOR SYSTEM VIBRATION ABSORBER 审中-公开
标题翻译：转子系统振动吸收器
公开(公告)号：WO2002085705A1
公开(公告)日：2002-10-31
申请号：PCT/US2002/012643
申请日：2002-04-19
申请人： BELL HELICOPTER TEXTRON INC. , SEHGAL, Ajay , COVINGTON, Cecil, E. , SMITH, Michael, R. , STAMPS, Frank, B. , MARSHALL, Bryan
发明人： SEHGAL, Ajay , COVINGTON, Cecil, E. , SMITH, Michael, R. , STAMPS, Frank, B. , MARSHALL, Bryan
IPC分类号： B64C27/51
CPC分类号： B64C27/51 , B64C27/001 , B64C2027/003 , Y10S416/50
摘要： A rotor system vibration absorber for use with a helicopter of other rotocraft is disclosed in which spring forces are provided by a plurality of elongated rods (73) arranged in a selected pattern. The rods are coupled at one end to a fixed base (79) that is coupled to a rotor hub (55), and at the other end to a tuning weight (81).
摘要翻译：公开了一种与其他旋转式飞机的直升机一起使用的转子系统减振器，其中弹簧力由以选定的图案排列的多个细长杆（73）提供。杆在一端连接到固定基座（79），该固定基座连接到转子毂（55），另一端连接到调谐重物（81）。

8. 发明申请

WO2016116478A1 THRUST-GENERATING ROTOR ASSEMBLY 审中-公开
标题翻译：制动转子总成
公开(公告)号：WO2016116478A1
公开(公告)日：2016-07-28
申请号：PCT/EP2016/051065
申请日：2016-01-20
申请人： PROX DYNAMICS AS
发明人： MUREN, Petter , MARTON, Trygve Frederik , JOHNSRUD, Ivar , HAGH SANDBERG, Pål
IPC分类号： B64C27/51 , A63H27/00 , B64C27/58 , B64C27/72
CPC分类号： B64C27/72 , A63H27/12 , B64C27/51 , B64C27/58 , B64C2201/024 , Y02T50/34
摘要： The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades.
摘要翻译：本发明公开了一种转子控制系统，其中转子转矩的快速变化被转移到在推力产生转子中作用在转子叶片的叶片俯仰轴线上的力矩中，以最终控制旋翼飞机的运动。作用在转子叶片上的力矩通过仔细调节的阻尼构件传递，以便允许转子扭矩的快速变化，从而产生叶片俯仰角的循环变化，同时缓慢或永久性的变化被抵消并影响转速和推力由转子产生，而不会永久影响各个转子叶片的叶片桨距角。

9. 发明申请

WO2016057215A1 ANTI-VIBRATION MOMENT GENERATING AIRCRAFT ACTUATION SYSTEM 审中-公开
标题翻译：抗振动发电机制动系统
公开(公告)号：WO2016057215A1
公开(公告)日：2016-04-14
申请号：PCT/US2015/051576
申请日：2015-09-23
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： HUNTER, David H. , WELSH, William A. , BASKIN, Bryan Kenneth , BUTLER, Chris Paul
IPC分类号： B64C27/00 , B64C27/08 , B64C27/51
CPC分类号： B64C27/001 , B64C27/10 , B64C27/12 , B64C2027/002 , B64C2027/004
摘要： An aircraft is provided and includes an airframe, an engine, a drive portion driven by the engine, a rotor apparatus, which includes a rotor rotatable relative to the airframe and a fairing, a gearbox disposed to transmit rotational energy from the drive portion to the rotor to drive the rotor to rotate relative to the airframe and which generates a rotor rotation vibration, support members by which the gearbox is disposed on the airframe and an actuation system including actuation elements disposed at the fairing, the actuation system being configured to generate an anti-vibration moment using the actuation elements disposed at the fairing to counter the rotor rotation vibration.
摘要翻译：提供飞机并包括机身，发动机，由发动机驱动的驱动部分，转子装置，其包括相对于机身可转动的转子和整流罩，齿轮箱被设置成将旋转能量从驱动部分传递到转子，以驱动转子相对于机身旋转并产生转子旋转振动，齿轮箱设置在机身上的支撑构件和包括设置在整流罩上的致动元件的致动系统，致动系统被配置为产生使用设置在整流罩上的致动元件来抵抗转子旋转振动的抗振动力矩。

10. 发明申请

WO2014100655A1 SYSTEM AND METHOD FOR LINKAGE LENGTH ADJUSTMENT 审中-公开
标题翻译：用于连接长度调整的系统和方法
公开(公告)号：WO2014100655A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/077071
申请日：2013-12-20
申请人： BELL HELICOPTER TEXTRON, INC.
发明人： WIINIKKA, Mark A.
IPC分类号： B64C27/51 , F16C7/06
CPC分类号： B64C27/51 , B64C27/008 , B64C27/32 , F16C11/0614
摘要： A rotor system has a rotor (302), an axis of rotation about which the rotor (302) may be rotated, a linkage system (310) having a first adjustable length portion (210) and a second adjustable length portion (212), wherein the second adjustable length portion (212) is configured to provide a relatively finer adjustment of an overall effective length of the linkage system (310) as compared to the first adjustable length portion (210) and wherein the rotor (302) is configured to rotate about the axis in response to changing the overall effective length of the linkage system (310).
摘要翻译：转子系统具有转子（302），转子（302）可以旋转的旋转轴线，具有第一可调节长度部分（210）和第二可调长度部分（212）的连杆系统（310）其中所述第二可调节长度部分（212）被配置为与所述第一可调整长度部分（210）相比提供所述连杆系统（310）的总有效长度的相对更精细的调整，并且其中所述转子（302）被配置为响应于改变连杆系统（310）的总有效长度，围绕轴旋转。

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