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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
Applicant: 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
Inventor： 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
Abstract: 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.
Abstract translation: 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。
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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
Applicant: 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.
Inventor： 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: B64C27/51
Abstract: 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.
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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
Applicant: BELL HELICOPTER TEXTRON INC. , SEHGAL, Ajay , COVINGTON, Cecil, E. , SMITH, Michael, R. , STAMPS, Frank, B. , MARSHALL, Bryan
Inventor： SEHGAL, Ajay , COVINGTON, Cecil, E. , SMITH, Michael, R. , STAMPS, Frank, B. , MARSHALL, Bryan
IPC: B64C27/51
CPC classification number: B64C27/51 , B64C27/001 , B64C2027/003 , Y10S416/50
Abstract: 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).
Abstract translation: 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）。
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公开(公告)号：WO2017209827A3
公开(公告)日：2017-12-07
申请号：PCT/US2017/022380
申请日：2017-03-14
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： CHOI, Jouyoung, Jason , HEVERLY, David , KIZHAKKEPAT, Amarjit, O. , PARHAM, Thomas , SEIFERT, Michael , SMITH, Michael , STAMPS, Frank, B. , GAY, Frederick, S.
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
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公开(公告)号：WO2012161680A1
公开(公告)日：2012-11-29
申请号：PCT/US2011/037395
申请日：2011-05-20
Applicant: BELL HELICOPTER TEXTRON INC. , STAMPS, Frank, B.
Inventor： STAMPS, Frank, B.
IPC: B64C27/02
CPC classification number: F01D7/00 , B64C11/06 , B64C11/32 , B64C27/605 , F04D29/362
Abstract: A blade-pitch control system for controlling a pitch angle of blades on a rotor has an input swashplate assembly having non-rotating and rotating portions, the rotating portion being operably connected to blade grips. A feedback swashplate assembly has non-rotating and rotating portions, the rotating portion being connected to the yoke for movement with the yoke during flapping of the yoke. Linear actuators connect the non-rotating portion of the input swashplate assembly to the non-rotating portion of the feedback swashplate assembly. Motion of the yoke during flapping causes a corresponding motion of the feedback swashplate assembly and input swashplate assembly for providing selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the grips.
Abstract translation: 用于控制转子上的叶片的桨距角的叶片桨距控制系统具有输入斜盘组件，其具有非旋转和旋转部分，旋转部分可操作地连接到叶片把手。 反馈斜盘组件具有非旋转和旋转部分，旋转部分连接到磁轭，以在磁轭摇动期间与磁轭一起运动。 线性致动器将输入斜盘组件的非旋转部分连接到反馈斜盘组件的非旋转部分。 在摇摆期间，轭的运动导致反馈旋转斜盘组件和输入斜盘组件的相应运动，以在轭的拍动运动和夹具的俯仰运动之间提供所选的俯仰角耦合。
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Patent Agency Ranking16.发明申请
公开(公告)号：WO2012064335A1
公开(公告)日：2012-05-18
申请号：PCT/US2010/056491
申请日：2010-11-12
Applicant: BELL HELICOPTER TEXTRON INC. , SHERRILL, Paul, B. , STAMPS, Frank, B. , MEASOM, Ronald, J.
Inventor： SHERRILL, Paul, B. , STAMPS, Frank, B. , MEASOM, Ronald, J.
CPC classification number: B64C27/473 , B29C70/30 , B29L2031/085 , B64C27/008 , B64C2027/4736 , Y02E10/721 , Y02P70/523 , Y10T428/24992
Abstract: A rotor blade for an aircraft includes a composite portion having fiber-reinforced resin material, the composite portion having an outside surface that forms at least a partial airfoil shape. The weighted portion includes a plurality of weighted material layers and a plurality of fiber-reinforced resin material layers. Weighted material is configured to be compatible with and integrated into composite manufacturing processes used to fabricate the rotor blade. The weighted portion has a higher density than the composite portion and positioned to produce desired mass balance characteristics of the rotor blade.
Abstract translation: 用于飞行器的转子叶片包括具有纤维增强树脂材料的复合部分，所述复合部分具有形成至少部分翼型的外表面。 加权部分包括多个加权材料层和多个纤维增强树脂材料层。 加权材料被配置为与用于制造转子叶片的复合制造工艺兼容并且被集成。 加重部分具有比复合部分更高的密度并且被定位成产生转子叶片的期望的质量平衡特性。
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公开(公告)号：WO2009088495A1
公开(公告)日：2009-07-16
申请号：PCT/US2008/050213
申请日：2008-01-04
Applicant: BELL HELICOPTER TEXTRON INC. , STAMPS, Frank, B. , TISDALE, Patrick, R.
Inventor： STAMPS, Frank, B. , TISDALE, Patrick, R.
IPC: B64C27/00
CPC classification number: B64C29/0033 , B64C27/32 , B64C27/41 , B64C2027/125 , F16D3/33 , Y10S464/904
Abstract: A constant-velocity drive system for an aircraft rotor has a gimbal mechanism and a differential torque-combining mechanism. The gimbal mechanism has gimbals driven in rotation by a rotor mast about a mast axis, the gimbals providing for gimballing relative to the mast about gimbal axes generally perpendicular to the mast axis. The differential torque-combining mechanism is connected to the gimbal mechanism and configured to be driven in rotation about the mast axis by the gimbal mechanism. The differential mechanism is capable of gimballing relative to the mast about the gimbal axes, the differential torque-combining mechanism having an output component attached to a yoke of the rotor for driving the yoke in rotation with the differential torque- combining mechanism.
Abstract translation: 用于飞行器转子的恒速驱动系统具有万向节机构和差动转矩组合机构。 万向节机构具有围绕桅杆轴线的转子桅杆旋转驱动的万向节，所述万向架相对于桅杆提供关于通常垂直于桅杆轴线的万向轴线的槌球。 差速转矩组合机构连接到万向节机构，并且构造成通过万向节机构围绕桅杆轴线旋转。 该差速机构能够相对于桅杆围绕万向轴进行槌球，该差速扭矩组合机构具有附接到转子的轭的输出部件，用于通过差速转矩组合机构来旋转该轭。
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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
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。
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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
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。
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公开(公告)号：WO1996017183A1
公开(公告)日：1996-06-06
申请号：PCT/US1994013971
申请日：1994-12-01
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： BELL HELICOPTER TEXTRON INC. , SMITH, Michael, R. , STAMPS, Frank, B.
IPC: F16F09/10
CPC classification number: F16F15/027 , F16F7/1005 , F16F13/08 , F16F15/02
Abstract: A tunable dual-axis live isolator (31) with a vertical single-axis isolator (33) and a horizontal single-axis isolator (35) with cruciform member (41) serving as pistons for both single-axis isolators (33-35). The isolator (31) is tuned by a sleeve (83) within the cruciform member (41) for varying the dimension of the tuning passage (75). The isolator (31) minimizes the transfer of vibration forces and moments from a vibrating body to a body attached thereto.
Abstract translation: 具有垂直单轴隔离器（33）和水平单轴隔离器（35）的可调谐双轴活动隔离器（31），其具有用作单轴隔离器（33-35）的活塞的十字形构件（41） 。 隔离器（31）由十字形构件（41）内的套筒（83）调节，以改变调谐通道（75）的尺寸。 隔离器（31）最小化从振动体到连接到其的身体的振动力和力矩的传递。
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