公开(公告)号：WO2008020848A2

公开(公告)日：2008-02-21

申请号：PCT/US2006032182

申请日：2006-08-17

Applicant: BELL HELICOPTER TEXTRON INC ,  STAMPS FRANK B ,  RAUBER RICHARD ,  POPELKA DAVID ,  TISDALE PAT ,  CAMPBELL TOM ,  BRASWELL JAMES LEE JR

Inventor： STAMPS FRANK B ,  RAUBER RICHARD ,  POPELKA DAVID ,  TISDALE PAT ,  CAMPBELL TOM ,  BRASWELL JAMES LEE JR

IPC: B64C27/12

CPC classification number: B64C27/32 ,  B64C27/35

Abstract: A torque coupling for a rotor head of a rotary-wing aircraft is configured for rotation with a mast and for causing rotation of an attached yoke. The coupling has trunnions that rotate with the mast and extend generally radially. Pad-bearing assemblies each have a central member coupled to one of the trunnions with a laminated spherical bearing and have laminated pad bearings affixed to opposing sides of the central member. The laminated bearings have alternating rigid and elastomeric layers. A bearing mount is affixed to each pad bearing and is connected to a yoke for rotating the yoke with the mast. The pad-bearing assemblies allow for relative motion between each central member and the associated trunnion and between each central member and the bearing mounts through elastic shear deformation, and this allows for gimballing of the attached yoke relative to the mast.

Abstract translation: 用于旋转翼飞行器的转子头的扭矩联接器构造成用桅杆旋转并且用于使附接的轭的旋转。 联轴器具有与桅杆一起旋转并且径向延伸的耳轴。 垫轴承组件各自具有与层叠的球面轴承联接到其中一个耳轴的中心构件，并且具有固定到中心构件的相对侧的层压垫轴承。 层压轴承具有交替的刚性和弹性层。 轴承座固定到每个垫轴承上，并连接到轭架上，用于使桅杆旋转。 垫片轴承组件允许在每个中心构件和相关联的耳轴之间以及通过弹性剪切变形在每个中心构件和轴承座之间进行相对运动，并且这允许相对于桅杆对附接的轭进行槌球。

公开(公告)号：WO2006132636A1

公开(公告)日：2006-12-14

申请号：PCT/US2005/019979

申请日：2005-06-07

Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  BRASWELL, James, L., Jr. ,  BASKIN, Charles, L. ,  ZIERER, Joe, J. ,  HAYNIE, David, A. ,  RAUBER, Richard, E. ,  CAMPBELL, Thomas ,  TISDALE, Patrick, R.

Inventor： STAMPS, Frank, B. ,  BRASWELL, James, L., Jr. ,  BASKIN, Charles, L. ,  ZIERER, Joe, J. ,  HAYNIE, David, A. ,  RAUBER, Richard, E. ,  CAMPBELL, Thomas ,  TISDALE, Patrick, R.

IPC: F16D3/48

CPC classification number: F16D3/48 ,  B64C27/14 ,  F16D3/28 ,  F16D3/78

Abstract: A constant-velocity joint is configured for use with a rotary-wing aircraft having at least one engine. A driver is coupled to an output shaft of the engine, the driver being rotatable about an axis. A yoke is at least partially rotatable relative to the driver about a first center of rotation, the center of rotation being located on the axis. A plurality of upright link couple the yoke to the driver, each ling being translatable relative to the yoke, the driver, or both. Each link is also rotatable relative to the yoke, the driver, or both, about a second center of rotation.

Abstract translation: 等速万向节被构造成与具有至少一个发动机的旋翼飞行器一起使用。 驾驶员联接到发动机的输出轴，驾驶员可绕轴线旋转。 轭围绕第一旋转中心相对于驾驶员至少部分可旋转，旋转中心位于轴上。 多个直立连接器将轭架耦合到驱动器，每个引线可相对于轭，驱动器或两者平移。 每个连杆也可相对于轭，驱动器或两者围绕第二旋转中心旋转。

公开(公告)号：WO2006081181A2

公开(公告)日：2006-08-03

申请号：PCT/US2006/002284

申请日：2006-01-24

Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  TISDALE, Patrick, R. ,  SHERRILL, Paul ,  RAUBER, Richard ,  CAMPBELL, Thomas, C. ,  BRASWELL, James, Lee, Jr. ,  MEASOM, Ron ,  HIROS, Tricia ,  POPELKA, David ,  SOUTHERLAND, Michael, J. ,  STANNEY, Keith ,  WASIKOWSKI, Mark ,  LEDBETTER, Tim

Inventor： STAMPS, Frank, B. ,  TISDALE, Patrick, R. ,  SHERRILL, Paul ,  RAUBER, Richard ,  CAMPBELL, Thomas, C. ,  BRASWELL, James, Lee, Jr. ,  MEASOM, Ron ,  HIROS, Tricia ,  POPELKA, David ,  SOUTHERLAND, Michael, J. ,  STANNEY, Keith ,  WASIKOWSKI, Mark ,  LEDBETTER, Tim

IPC: B64C27/50

CPC classification number: B64C27/48 ,  B64C27/33

Abstract: An assembly for providing flexure to a blade of a rotary blade system includes 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 has a layer of cushioning material positioned thereon and secured thereto. An alternate embodiment includes 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. Another alternate embodiment includes a similar assembly having a twist-shank type of yoke for providing rotation of attached blades about their respective pitch axes.

Abstract translation: 用于向旋转刀片系统的刀片提供挠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轭。 上和下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。 替代实施例包括用于向旋转刀片系统的刀片提供挠曲的组件，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件 其中一个弯曲表面是不形成圆周的一部分的非圆弧。 另一替代实施例包括具有扭转柄类型的轭的类似组件，用于提供附接刀片围绕它们各自的俯仰轴的旋转。

公开(公告)号：WO2008133614A1

公开(公告)日：2008-11-06

申请号：PCT/US2007/010109

申请日：2007-04-24

Applicant: BELL HELICOPTER TEXTRON INC. ,  RAUBER, Richard, E. ,  POPELKA, David, A. ,  STAMPS, Frank, B.

Inventor： RAUBER, Richard, E. ,  POPELKA, David, A. ,  STAMPS, Frank, B.

IPC: B64C27/32 ,  F16C15/00

CPC classification number: B64C27/32 ,  B06B1/164 ,  B64C27/001 ,  B64C2027/003 ,  B64C2027/004 ,  F16F7/1011 ,  F16F15/14

Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency.

Abstract translation: 用于飞行器的振动衰减器具有安装在飞行器的转子轮毂的旋转系统中的至少一个重量，每个重量可围绕毂相对于轮毂的旋转轴线和彼此的重量旋转。 提供驱动装置，用于以选定的速度围绕旋转轴线旋转每个重量，以产生相对于和衰减具有所选频率的转子引起的振动的振荡剪切力。

公开(公告)号：WO2008048206A3

公开(公告)日：2008-10-30

申请号：PCT/US2006023895

申请日：2006-06-20

Applicant: BELL HELICOPTER TEXTRON INC ,  STAMPS FRANK B ,  RAUBER RICHARD

Inventor： STAMPS FRANK B ,  RAUBER RICHARD

IPC: B63H1/00

CPC classification number: B64C27/35 ,  F16F1/40

Abstract: A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed.

Abstract translation: 公开了具有用于提供稳定俯仰力矩的装置的离心力轴承。 离心力轴承可以可选地包括锥形装置。 公开了一种具有离心力轴承的转子系统。 公开了一种具有离心力轴承的转翼飞机。

公开(公告)号：WO2008048206A2

公开(公告)日：2008-04-24

申请号：PCT/US2006/023895

申请日：2006-06-20

Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  RAUBER, Richard

Inventor： STAMPS, Frank, B. ,  RAUBER, Richard

IPC: B64C27/51

CPC classification number: B64C27/35 ,  F16F1/40

Abstract: A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed.

Abstract translation: 公开了一种具有用于提供稳定俯仰力矩的装置的离心力轴承。 离心力轴承可以可选地包括锥形装置。 公开了一种具有离心力轴承的转子系统。 公开了一种具有离心力轴承的旋翼飞机。

公开(公告)号：WO2008045011A9

公开(公告)日：2008-04-17

申请号：PCT/US2006/019388

申请日：2006-05-19

Applicant: BELL HELICOPTER TEXTRON INC. ,  RAUBER, Richard ,  STAMPS, Frank, B. ,  BRASWELL, James, Lee, Jr.

Inventor： RAUBER, Richard ,  STAMPS, Frank, B. ,  BRASWELL, James, Lee, Jr.

IPC: B64C27/22

Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque- splitting mechanism and a gimbal mechanism is disclosed.

公开(公告)号：WO2008045011A2

公开(公告)日：2008-04-17

申请号：PCT/US2006019388

申请日：2006-05-19

Applicant: BELL HELICOPTER TEXTRON INC ,  RAUBER RICHARD ,  STAMPS FRANK B ,  BRASWELL JAMES LEE JR

Inventor： RAUBER RICHARD ,  STAMPS FRANK B ,  BRASWELL JAMES LEE JR

IPC: B64C27/35

CPC classification number: B64C27/41 ,  B64C27/52 ,  B64C29/0033 ,  F16C1/04

Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque- splitting mechanism and a gimbal mechanism is disclosed.

Abstract translation: 公开了一种用于旋转翼飞行器转子的恒速驱动系统，其包括差动转矩分解机构和万向架机构。 公开了具有旋转翼飞行器转子的旋转翼飞机，其包括差动扭矩分离机构和万向架机构。

公开(公告)号：WO2007081337A2

公开(公告)日：2007-07-19

申请号：PCT/US2006001082

申请日：2006-01-13

Applicant: BELL HELICOPTER TEXTRON INC ,  STAMPS FRANK B ,  RAUBER RICHARD E

Inventor： STAMPS FRANK B ,  RAUBER RICHARD E

IPC: B64C27/32

CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C27/82

Abstract: A rotor-hub for a rotary-wing aircraft is disclosed. The rotor-hub comprises a yoke comprising a plurality of yoke arms and a plurality of yoke straps, wherein the yoke arms are joined together by the yoke straps, and wherein a plurality of inner walls of the yoke define a central void space. A pitch horn is movably connected to the yoke and a portion of the pitch horn is located within the central void space. A connecting shell is fixedly attached to the yoke.

Abstract translation: 公开了用于旋转翼飞机的转子轮毂。 所述转子轮毂包括轭架，所述轭架包括多个轭架臂和多个轭架条，其中所述轭架臂通过所述轭架条连接在一起，并且其中所述轭架的多个内壁限定中央空隙空间。 变幅杆可移动地连接到轭，并且变幅杆的一部分位于中央空隙空间内。 连接壳体固定地连接到轭。

公开(公告)号：WO2010082937A1

公开(公告)日：2010-07-22

申请号：PCT/US2009/031388

申请日：2009-01-19

Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  RAUBER, Richard, E.

Inventor： STAMPS, Frank, B. ,  RAUBER, Richard, E.

IPC: B64C27/605

CPC classification number: B64C27/32 ,  B64C27/605

Abstract: A blade-pitch control system has a swashplate configured for continuous rotation with an associated rotor and mast, and at least one link connects the swashplate to each blade of the rotor. The swashplate provides for collective control of the pitch angle of the blades through selective rotation of the swashplate about a swashplate axis while the swashplate is rotating with the rotor and mast. The system can be configured to provide for cyclic control of the pitch angle of the blades through planar translation of the swashplate or through tilting of the swashplate about axes generally perpendicular to the swashplate axis.

Abstract translation: 桨叶桨距控制系统具有构造成与相关联的转子和桅杆连续旋转的斜盘，并且至少一个连杆将旋转斜盘连接到转子的每个叶片。 旋转斜盘通过旋转斜盘围绕斜盘轴线的选择性旋转而提供叶片桨距角的集中控制，同时斜盘与转子和桅杆一起旋转。 该系统可以被配置成通过斜盘的平面平移或者通常围绕通常垂直于斜盘轴线的轴线倾斜旋转斜盘来提供叶片的桨距角的循环控制。