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    ELECTROMECHANICAL ROTARY ACTUATOR AND METHOD
    1.
    发明申请
    ELECTROMECHANICAL ROTARY ACTUATOR AND METHOD 有权
    电动旋转执行机构及方法

    公开(公告)号：US20130320782A1

    公开(公告)日：2013-12-05

    申请号：US13484689

    申请日：2012-05-31

    申请人： Claude G. Matalanis ,  Andrzej Ernest Kuczek ,  Ulf J. Jonsson ,  Brian E. Wake ,  Zaffir A. Chaudhry ,  Paul Brewer

    发明人： Claude G. Matalanis ,  Andrzej Ernest Kuczek ,  Ulf J. Jonsson ,  Brian E. Wake ,  Zaffir A. Chaudhry ,  Paul Brewer

    IPC分类号： H02K7/116 ,  H02K15/00

    CPC分类号： H02K5/1732 ,  B64C2027/7266 ,  H02K7/14 ,  Y02T50/34 ,  Y10T29/49009

    摘要： An electromechanical rotary actuator including a housing including first end that extends to a second end through an intermediate portion that defines a longitudinal axis, and an internal cavity. An electric motor is arranged within the internal cavity. The electric motor includes a shaft having first shaft end and a second shaft end. A drive member is arranged within the housing along the longitudinal axis. The drive member includes an input shaft operatively coupled to the first shaft end and an output shaft. An output shaft member is coupled to the output shaft of the drive member. At least one bearing assembly supports one of the output shaft member and the first shaft end, and a preload member is arranged within the housing and configured to apply a compressive axial force to the at least one bearing, the drive member and the electric motor.

    摘要翻译： 一种机电旋转致动器，包括壳体，该壳体包括通过限定纵向轴线的中间部分延伸到第二端的第一端和内部空腔。 电动机设置在内腔内。 电动机包括具有第一轴端和第二轴端的轴。 驱动构件沿着纵向轴线布置在壳体内。 驱动构件包括可操作地联接到第一轴端的输入轴和输出轴。 输出轴构件联接到驱动构件的输出轴。 至少一个轴承组件支撑输出轴构件和第一轴端中的一个，并且预紧构件布置在壳体内并构造成向至少一个轴承，驱动构件和电动马达施加压缩轴向力。

    Electromechanical rotary actuator and method
    2.
    发明授权
    Electromechanical rotary actuator and method 有权
    机电式旋转执行机构及方法

    公开(公告)号：US09407121B2

    公开(公告)日：2016-08-02

    申请号：US13484689

    申请日：2012-05-31

    申请人： Claude G. Matalanis ,  Andrzej Ernest Kuczek ,  Ulf J. Jonsson ,  Brian E. Wake ,  Zaffir A. Chaudhry ,  Paul Brewer

    发明人： Claude G. Matalanis ,  Andrzej Ernest Kuczek ,  Ulf J. Jonsson ,  Brian E. Wake ,  Zaffir A. Chaudhry ,  Paul Brewer

    IPC分类号： H02K15/00 ,  H02K5/173 ,  H02K7/14

    CPC分类号： H02K5/1732 ,  B64C2027/7266 ,  H02K7/14 ,  Y02T50/34 ,  Y10T29/49009

    摘要： An electromechanical rotary actuator including a housing including first end that extends to a second end through an intermediate portion that defines a longitudinal axis, and an internal cavity. An electric motor is arranged within the internal cavity. The electric motor includes a shaft having first shaft end and a second shaft end. A drive member is arranged within the housing along the longitudinal axis. The drive member includes an input shaft operatively coupled to the first shaft end and an output shaft. An output shaft member is coupled to the output shaft of the drive member. At least one bearing assembly supports one of the output shaft member and the first shaft end, and a preload member is arranged within the housing and configured to apply a compressive axial force to the at least one bearing, the drive member and the electric motor.

    摘要翻译： 一种机电旋转致动器，包括壳体，该壳体包括通过限定纵向轴线的中间部分延伸到第二端的第一端和内部空腔。 电动机设置在内腔内。 电动机包括具有第一轴端和第二轴端的轴。 驱动构件沿着纵向轴线布置在壳体内。 驱动构件包括可操作地联接到第一轴端的输入轴和输出轴。 输出轴构件联接到驱动构件的输出轴。 至少一个轴承组件支撑输出轴构件和第一轴端中的一个，并且预紧构件布置在壳体内并构造成向至少一个轴承，驱动构件和电动马达施加压缩轴向力。

    Hybrid actuator for helicopter rotor blade control flaps
    6.
    发明授权
    Hybrid actuator for helicopter rotor blade control flaps 有权
    用于直升机转子叶片控制翼片的混合致动器

    公开(公告)号：US07762770B2

    公开(公告)日：2010-07-27

    申请号：US11638980

    申请日：2006-12-14

    申请人： Fanping Sun ,  Zaffir A. Chaudhry ,  Jimmy Lih-Min Yeh ,  Michael G. O'Callaghan ,  Ulf J. Jonsson ,  Brian E. Wake ,  Robert H. Dold

    发明人： Fanping Sun ,  Zaffir A. Chaudhry ,  Jimmy Lih-Min Yeh ,  Michael G. O'Callaghan ,  Ulf J. Jonsson ,  Brian E. Wake ,  Robert H. Dold

    IPC分类号： B64C27/615

    CPC分类号： B64C27/615 ,  B64C2027/7294 ,  Y02T50/34

    摘要： A helicopter rotor blade that has a blade body and a control flap secured to the blade body. The rotor blade has a first primary mover capable of generating a first linear motion that is sufficient to generate a high amplitude, low frequency motion of the control flap; and a second primary mover capable of generating a second linear motion that is sufficient to generate a small amplitude, high frequency motion of the control flap. Further, the rotor blade has a coupling transmission for combining the first linear motion with the second linear motion that generates a cumulative linear motion; and a second transmission device that causes the cumulative linear motion to rotate the control flap.

    摘要翻译： 一种直升机转子叶片，其具有固定到叶片本体的叶片体和控制翼。 转子叶片具有能够产生足以产生控制翼片的高振幅，低频运动的第一线性运动的第一原动机; 以及能够产生足以产生控制翼片的小振幅，高频运动的第二线性运动的第二原动机。 此外，转子叶片具有用于将第一线性运动与产生累积线性运动的第二线性运动相结合的联接传动装置; 以及使累积线性运动使控制翼片旋转的第二传动装置。

    Hybrid actuator for helicopter rotor blade control flaps
    7.
    发明申请
    Hybrid actuator for helicopter rotor blade control flaps 有权
    用于直升机转子叶片控制翼片的混合致动器

    公开(公告)号：US20080145221A1

    公开(公告)日：2008-06-19

    申请号：US11638980

    申请日：2006-12-14

    申请人： Fanping Sun ,  Zaffir A. Chaudhry ,  Jimmy Lih-Min Yeh ,  Michael G. O'Callaghan ,  Ulf J. Jonsson ,  Brian E. Wake ,  Robert H. Dold

    发明人： Fanping Sun ,  Zaffir A. Chaudhry ,  Jimmy Lih-Min Yeh ,  Michael G. O'Callaghan ,  Ulf J. Jonsson ,  Brian E. Wake ,  Robert H. Dold

    IPC分类号： F01D7/00

    CPC分类号： B64C27/615 ,  B64C2027/7294 ,  Y02T50/34

    摘要： A helicopter rotor blade that has a blade body and a control flap secured to the blade body. The rotor blade has a first primary mover capable of generating a first linear motion that is sufficient to generate a high amplitude, low frequency motion of the control flap; and a second primary mover capable of generating a second linear motion that is sufficient to generate a small amplitude, high frequency motion of the control flap. Further, the rotor blade has a coupling transmission for combining the first linear motion with the second linear motion that generates a cumulative linear motion; and a second transmission device that causes the cumulative linear motion to rotate the control flap.

    摘要翻译： 一种直升机转子叶片，其具有固定到叶片本体的叶片体和控制翼。 转子叶片具有能够产生足以产生控制翼片的高振幅，低频运动的第一线性运动的第一原动机; 以及能够产生足以产生控制翼片的小振幅，高频运动的第二线性运动的第二原动机。 此外，转子叶片具有用于将第一线性运动与产生累积线性运动的第二线性运动相结合的联接传动装置; 以及使累积线性运动使控制翼片旋转的第二传动装置。

    Active rotor blade control effector system for a rotary-wing aircraft
    9.
    发明授权
    Active rotor blade control effector system for a rotary-wing aircraft 有权
    用于旋翼飞机的主动转子叶片控制效应器系统

    公开(公告)号：US08596974B2

    公开(公告)日：2013-12-03

    申请号：US12910554

    申请日：2010-10-22

    申请人： Claude G. Matalanis ,  Brian E. Wake

    发明人： Claude G. Matalanis ,  Brian E. Wake

    IPC分类号： B64C11/00

    CPC分类号： B64C27/615 ,  B64C2003/145 ,  B64C2027/7266 ,  Y02T50/34

    摘要： A helicopter includes an airframe, and a rotor system mounted to the airframe. The rotor system includes a plurality of rotor blades. Each of the plurality of rotor blades includes a root portion that extends to a tip portion through an airfoil portion. The airfoil portion includes first and second surfaces. An effector is mounted within the airfoil portion of at least one of the plurality of rotor blades. The effector includes a first end portion that extends to a second end portion through an intermediate portion, and a flap arranged at the second end portion. The effector is selectively actuated to shift from a first, stowed, position wherein the flap is positioned within the at least one rotor blade to a second, deployed, position, wherein flap projects through at least one of the first and second surfaces of the at least one rotor blade.

    摘要翻译： 一架直升机包括机身和安装在机身上的转子系统。 转子系统包括多个转子叶片。 多个转子叶片中的每一个包括通过翼型部延伸到尖端部分的根部。 机翼部分包括第一和第二表面。 效应器安装在多个转子叶片中的至少一个转子叶片的翼型部分内。 效应器包括通过中间部分延伸到第二端部的第一端部分和布置在第二端部处的折翼。 效应器被选择性地致动以从第一，收起的位置移动，其中所述翼片被定位在所述至少一个转子叶片内的第二，展开位置，其中翼片突出穿过所述第一和第二表面中的至少一个， 至少一个转子叶片。

    ACTIVE ROTOR BLADE CONTROL EFFECTOR SYSTEM FOR A ROTARY-WING AIRCRAFT
    10.
    发明申请
    ACTIVE ROTOR BLADE CONTROL EFFECTOR SYSTEM FOR A ROTARY-WING AIRCRAFT 有权
    用于旋转飞行器的主动转子叶片控制效应器系统

    公开(公告)号：US20110164976A1

    公开(公告)日：2011-07-07

    申请号：US12910554

    申请日：2010-10-22

    申请人： Claude G. Matalanis ,  Brian E. Wake

    发明人： Claude G. Matalanis ,  Brian E. Wake

    IPC分类号： B64C27/615

    CPC分类号： B64C27/615 ,  B64C2003/145 ,  B64C2027/7266 ,  Y02T50/34

    摘要： A helicopter includes an airframe, and a rotor system mounted to the airframe. The rotor system includes a plurality of rotor blades. Each of the plurality of rotor blades includes a root portion that extends to a tip portion through an airfoil portion. The airfoil portion includes first and second surfaces. An effector is mounted within the airfoil portion of at least one of the plurality of rotor blades. The effector includes a first end portion that extends to a second end portion through an intermediate portion, and a flap arranged at the second end portion. The effector is selectively actuated to shift from a first, stowed, position wherein the flap is positioned within the at least one rotor blade to a second, deployed, position, wherein flap projects through at least one of the first and second surfaces of the at least one rotor blade.

    摘要翻译： 一架直升机包括机身和安装在机身上的转子系统。 转子系统包括多个转子叶片。 多个转子叶片中的每一个包括通过翼型部延伸到尖端部分的根部。 机翼部分包括第一和第二表面。 效应器安装在多个转子叶片中的至少一个转子叶片的翼型部分内。 效应器包括通过中间部分延伸到第二端部的第一端部分和布置在第二端部处的折翼。 效应器被选择性地致动以从第一，收起的位置移动，其中所述翼片被定位在所述至少一个转子叶片内的第二，展开位置，其中翼片突出穿过所述第一和第二表面中的至少一个， 至少一个转子叶片。