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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。

    ACTIVE ROTOR BLADE CONTROL EFFECTOR SYSTEM FOR A ROTARY-WING AIRCRAFT
    5.
    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。

    Active rotor blade control effector system for a rotary-wing aircraft
    6.
    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。

    Low drag high restoring moment airfoils
    7.
    发明授权
    Low drag high restoring moment airfoils 有权
    低阻力高恢复力矩翼型

    公开(公告)号：US09132914B2

    公开(公告)日：2015-09-15

    申请号：US13561399

    申请日：2012-07-30

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

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

    IPC分类号： B64C7/00 ,  B64C27/10 ,  B64C23/00

    CPC分类号： B64C27/10 ,  B64C7/00 ,  B64C23/00

    摘要： A rotor hub fairing system for use in a counter-rotating, coaxial rotary wing aircraft is provided including an upper hub fairing defined about an axis. A lower hub fairing is similarly defined about the axis. An airfoil shaped shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The airfoil shaped shaft fairing has a thickness to chord (t/c) ratio in the range of about 20% and about 45%.

    摘要翻译： 提供了一种用于逆向旋转同轴旋转翼飞行器的转子轮毂整流罩系统，其包括围绕轴线限定的上部轮毂整流罩。 下部轮毂整流罩类似地定义在轴上。 上部翼形整流罩和下部轮毂整流罩之间设置翼型轴整流罩。 翼型整流罩的厚度与弦（t / c）的比值在约20％和约45％之间。

    LOW DRAG HIGH RESTORING MOMENT AIRFOILS
    8.
    发明申请
    LOW DRAG HIGH RESTORING MOMENT AIRFOILS 有权
    LOW DRAG高恢复动力飞行器

    公开(公告)号：US20140030103A1

    公开(公告)日：2014-01-30

    申请号：US13561399

    申请日：2012-07-30

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

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

    IPC分类号： B64C27/46

    CPC分类号： B64C27/10 ,  B64C7/00 ,  B64C23/00

    摘要： A rotor hub fairing system for use in a counter-rotating, coaxial rotary wing aircraft is provided including an upper hub fairing defined about an axis. A lower hub fairing is similarly defined about the axis. An airfoil shaped shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The airfoil shaped shaft fairing has a thickness to chord (t/c) ratio in the range of about 20% and about 45%.

    摘要翻译： 提供了一种用于逆向旋转同轴旋转翼飞行器的转子轮毂整流罩系统，其包括围绕轴线限定的上部轮毂整流罩。 下部轮毂整流罩类似地定义在轴上。 上部翼形整流罩和下部轮毂整流罩之间设置翼型轴整流罩。 翼型整流罩的厚度与弦（t / c）的比值在约20％和约45％之间。