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    Yoke for helicopter rotor systems
    1.
    发明授权
    Yoke for helicopter rotor systems 失效
    直升机转子系统的轭

    公开(公告)号：US5358381A

    公开(公告)日：1994-10-25

    申请号：US34345

    申请日：1993-03-19

    申请人： Cecil E. Covington ,  Timothy K. Ledbetter ,  Ernest A. Powell ,  Madison K. Robinson ,  Ajay Sehgal ,  Patrick R. Tisdale

    发明人： Cecil E. Covington ,  Timothy K. Ledbetter ,  Ernest A. Powell ,  Madison K. Robinson ,  Ajay Sehgal ,  Patrick R. Tisdale

    IPC分类号： B29C70/86 ,  B64C27/33 ,  B64C27/38

    CPC分类号： B64C27/33 ,  B29C70/86 ,  B29K2105/101 ,  B29L2031/08

    摘要： An improved feathering flexure for a helicopter rotor system yoke includes, in transverse cross section, a relatively thin central web and six relatively thin flanges. Three flanges extend from each of the web's two edges, and the flanges lie in planes which are approximately radial relative to the neutral feathering axis of the feathering flexure. The feathering flexure is constructed of fiberglass material embedded in a polymer matrix. The web's fiberglass material in the web is bias material, that is, material whose glass fibers are oriented at plus or minus 45 degrees relative to the yoke's spanwise axis. In transverse cross section, each of the flanges includes two unidirectional belts disposed on either side of a bias pack. The glass fibers in the unidirectional belts are oriented parallel to the yoke's spanwise axis. The fiberglass material in the bias packs is bias material. Each flange's unidirectional belts taper inwardly toward its bias pack adjacent to web, thereby decreasing the thickness of the flange adjacent to the web. In addition, the portion of each flange adjacent to the web is configured to minimize torsional rigidity and shear stress resulting from twisting the feathering flexure.

    摘要翻译： 用于直升机转子系统轭的改进的羽化挠曲在横截面中包括相对薄的中心腹板和六个相对薄的凸缘。 三个凸缘从每个腹板的两个边缘延伸，并且凸缘位于相对于羽化挠曲件的中性羽化轴线大致径向的平面中。 羽化挠曲由嵌入聚合物基体中的玻璃纤维材料构成。 幅材中的纤维网玻璃纤维材料是偏压材料，即玻璃纤维相对于轭的翼展轴线以正或负45度取向的材料。 在横截面中，每个凸缘包括设置在偏置组件的任一侧上的两个单向皮带。 单向带中的玻璃纤维平行于轭的翼展轴定向。 偏置组件中的玻璃纤维材料是偏压材料。 每个凸缘的单向带向内逐渐朝着与卷材相邻的偏压组件向内逐渐变细，从而减小了与卷材相邻的凸缘的厚度。 另外，与腹板相邻的每个凸缘的部分被构造成使扭转刚度和由于弯曲挠曲而产生的剪切应力最小化。

    Multiple-Yoke Main Rotor Assembly
    4.
    发明申请
    Multiple-Yoke Main Rotor Assembly 有权
    多重主转子总成

    公开(公告)号：US20130149151A1

    公开(公告)日：2013-06-13

    申请号：US13324363

    申请日：2011-12-13

    申请人： Richard E. Rauber ,  Frank B. Stamps ,  David A. Popelka ,  Patrick R. Tisdale ,  Tommie L. Wood

    发明人： Richard E. Rauber ,  Frank B. Stamps ,  David A. Popelka ,  Patrick R. Tisdale ,  Tommie L. Wood

    IPC分类号： B64C27/43 ,  B64C27/39

    CPC分类号： B64C27/43 ,  B64C29/0033

    摘要： The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.

    摘要翻译： 本申请包括用于飞机的主转子组件。 转子组件具有构造成围绕桅杆轴线旋转的主转子桅杆和两个枢转地连接到桅杆的轭架，用于围绕桅杆轴线旋转。 每个轭体可相对于桅杆独立地枢转，围绕大体上垂直于桅杆轴线的至少一个翼片轴线。 在至少一个实施例中，扭矩分配器连接轭，并且允许轭围绕桅杆轴线相对于彼此受到有限的旋转。 每个轭被构造成用于附接相对于桅杆轴线大致径向延伸的转子叶片。

    Stiff-in-plane rotor configuration
    6.
    发明授权
    Stiff-in-plane rotor configuration 有权
    刚体平面转子配置

    公开(公告)号：US08956117B2

    公开(公告)日：2015-02-17

    申请号：US13144448

    申请日：2009-01-19

    申请人： Frank B. Stamps ,  Patrick R. Tisdale ,  Tom Donovan ,  Richard E. Rauber

    发明人： Frank B. Stamps ,  Patrick R. Tisdale ,  Tom Donovan ,  Richard E. Rauber

    IPC分类号： B64C27/33 ,  B64C27/32

    CPC分类号： B64C27/35 ,  B64C27/32 ,  B64C27/33 ,  B64C27/39 ,  B64C27/48

    摘要： A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.

    摘要翻译： 一种用于旋转翼飞行器的转子组件，该转子具有中心轮毂组件，其具有带有多个臂的挠曲型扭转柄轭，每个臂适于安装在其上的转子叶片。 臂通过扭转相应的俯仰轴线的臂的部分来提供附接到轭的叶片的桨距变化。 与每个臂相关联的内侧变桨轴承附接到轮毂组件并且允许所附接的叶片围绕俯仰轴线旋转，内侧变桨轴承还允许臂相对于轮毂组件的平面外运动绕一个 拍动轴。 与每个臂相关联的外侧变桨轴承从相对于内侧变桨轴承的选定距离附接到相关联的臂，并且允许所附接的叶片围绕桨距轴线旋转。

    Aircraft Rotor with Discrete Flap Hinge
    7.
    发明申请
    Aircraft Rotor with Discrete Flap Hinge 有权
    飞机转子与离散瓣铰链

    公开(公告)号：US20130287576A1

    公开(公告)日：2013-10-31

    申请号：US13455814

    申请日：2012-04-25

    申请人： Frank B. Stamps ,  David A. Popelka ,  Tom Donovan ,  Patrick R. Tisdale ,  Richard E. Rauber

    发明人： Frank B. Stamps ,  David A. Popelka ,  Tom Donovan ,  Patrick R. Tisdale ,  Richard E. Rauber

    IPC分类号： B64C27/54

    CPC分类号： B64C27/39 ,  B64C27/48

    摘要： An aircraft rotor assembly has upper and lower hub plates adapted to be mounted to a central rotor mast for rotation therewith. A plurality of radial arms is connected to at least two flap bearings mounted between the hub plates and forming a discrete flap hinge, each flap hinge defining a flap axis and allowing rotation of the associated arm relative to the hub plates and about the corresponding flap axis. Each of a plurality of blade grips is rotatably connected to one of the arms for rotation about a pitch axis and adapted for mounting of a blade to each blade grip, such that each blade is capable of rotation with the grip about the pitch axis and capable of rotation together with the corresponding arm relative to the hub plates and about the corresponding flap axis.

    摘要翻译： 飞机转子组件具有适于安装到中心转子桅杆上的上和下毂板，以与其一起旋转。 多个径向臂连接到安装在轮毂板之间并形成离散的翼片铰链的至少两个翼片轴承，每个翼片铰链限定翼片轴线并允许相关联的臂相对于轮毂板和相应翼片轴线的旋转 。 多个叶片夹具中的每一个可旋转地连接到一个臂上，用于围绕俯仰轴线旋转，并适于将叶片安装到每个叶片手柄上，使得每个叶片能够围绕俯仰轴线旋转，并且能够 与相应的臂相对于轮毂板和围绕相应的翼片轴线旋转。

    Aircraft rotor with discrete flap hinge
    9.
    发明授权
    Aircraft rotor with discrete flap hinge 有权
    具有离散翼片铰链的飞机转子

    公开(公告)号：US09352830B2

    公开(公告)日：2016-05-31

    申请号：US13455814

    申请日：2012-04-25

    申请人： Frank B. Stamps ,  David A. Popelka ,  Tom Donovan ,  Patrick R. Tisdale ,  Richard E. Rauber

    发明人： Frank B. Stamps ,  David A. Popelka ,  Tom Donovan ,  Patrick R. Tisdale ,  Richard E. Rauber

    IPC分类号： B64C27/39 ,  B64C27/48

    CPC分类号： B64C27/39 ,  B64C27/48

    摘要： An aircraft rotor assembly has upper and lower hub plates adapted to be mounted to a central rotor mast for rotation therewith. A plurality of radial arms is connected to at least two flap bearings mounted between the hub plates and forming a discrete flap hinge, each flap hinge defining a flap axis and allowing rotation of the associated arm relative to the hub plates and about the corresponding flap axis. Each of a plurality of blade grips is rotatably connected to one of the arms for rotation about a pitch axis and adapted for mounting of a blade to each blade grip, such that each blade is capable of rotation with the grip about the pitch axis and capable of rotation together with the corresponding arm relative to the hub plates and about the corresponding flap axis.

    摘要翻译： 飞机转子组件具有适于安装到中心转子桅杆上的上和下毂板，以与其一起旋转。 多个径向臂连接到安装在轮毂板之间并形成离散的翼片铰链的至少两个翼片轴承，每个翼片铰链限定翼片轴线并允许相关联的臂相对于轮毂板和相应翼片轴线的旋转 。 多个叶片夹具中的每一个可旋转地连接到一个臂上，用于围绕俯仰轴线旋转，并适于将叶片安装到每个叶片手柄上，使得每个叶片能够围绕俯仰轴线旋转，并且能够 与相应的臂相对于轮毂板和围绕相应的翼片轴线旋转。

    Constant-Velocity Joint with Torque-Combining Differential
    10.
    发明申请
    Constant-Velocity Joint with Torque-Combining Differential 有权
    具有扭矩组合差速器的恒速接头

    公开(公告)号：US20110315816A1

    公开(公告)日：2011-12-29

    申请号：US13227917

    申请日：2011-09-08

    申请人： Frank B. Stamps ,  Patrick R. Tisdale

    发明人： Frank B. Stamps ,  Patrick R. Tisdale

    IPC分类号： B64D35/00 ,  B64C27/12

    CPC分类号： B64C29/0033 ,  B64C27/32 ,  B64C27/41 ,  B64C2027/125 ,  F16D3/33 ,  Y10S464/904

    摘要： 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.

    摘要翻译： 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。 差速机构能够相对于桅杆围绕万向轴进行槌球，差动转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旋转驱动轭。