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    LOCKING MANUAL DRIVE UNIT FOR AIRCRAFT ENGINE NACELLE DOOR OPERATING SYSTEM
    2.
    发明申请
    LOCKING MANUAL DRIVE UNIT FOR AIRCRAFT ENGINE NACELLE DOOR OPERATING SYSTEM 有权
    用于飞机发动机NACELLE门操作系统的锁定手动驱动单元

    公开(公告)号：US20160312511A1

    公开(公告)日：2016-10-27

    申请号：US14803305

    申请日：2015-07-20

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Kevin K. Chakkera ,  Timm E. Hartman ,  Ron Vaughan ,  Stephen Birn

    IPC: E05F11/02 ,  E05F15/00 ,  B64D29/08 ,  F16H1/20

    CPC classification number: F16H1/203 ,  B64C1/1446 ,  B64D29/06 ,  B64D29/08 ,  F02K1/763 ,  F16H1/22 ,  F16H25/2454

    Abstract: An aircraft engine nacelle door operating system locking manual drive unit includes a housing, an input drive shaft, an output drive shaft, a lock shaft, and a lock spring. The input drive shaft, the output drive shaft, and the lock shaft are all rotationally mounted in the housing. The output drive shaft continuously engages and mates with the input drive shaft, and he lock shaft extends at least partially into and engages the input drive shaft. The lock shaft is movable between a lock position, in which it engages and mates with the output drive shaft, and an unlock position, in it is disengaged from the output drive shaft. The lock spring supplies a bias force to the lock shaft that urges the lock shaft toward the lock position.

    Abstract translation: 飞机发动机舱门操作系统锁定手动驱动单元包括壳体，输入驱动轴，输出驱动轴，锁定轴和锁定弹簧。 输入驱动轴，输出驱动轴和锁定轴都旋转地安装在外壳中。 输出驱动轴与输入驱动轴连续地接合并配合，并且其锁定轴至少部分地延伸并接合输入驱动轴。 锁定轴可在其与输出驱动轴接合并配合的锁定位置之间移动，并且解锁位置在其中与输出驱动轴分离。 锁定弹簧向锁定轴提供偏压力，以将锁定轴朝向锁定位置。

    ACTUATOR INCLUDING HANDLING-PROOF POSITION FEEDBACK MECHANISM
    3.
    发明申请
    ACTUATOR INCLUDING HANDLING-PROOF POSITION FEEDBACK MECHANISM 审中-公开
    执行机构包括处理机构位置反馈机制

    公开(公告)号：US20170059020A1

    公开(公告)日：2017-03-02

    申请号：US15351967

    申请日：2016-11-15

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Ron Vaughan ,  Kevin K. Chakkera ,  Paul T. Wingett

    IPC: F16H25/22

    CPC classification number: F16H25/2204 ,  F16H2025/204 ,  F16H2025/2084 ,  F16H2025/2093 ,  Y10T74/18576

    Abstract: An actuator includes a housing assembly, an actuator shaft, an actuation member, and an anti-rotation rod. The actuator shaft is rotationally mounted in the housing assembly, is adapted to receive a drive torque, and is configured, upon receipt of the drive torque, to rotate. The actuation member is mounted on the actuator shaft, and is configured to translate in response to rotation of the actuator shaft. The anti-rotation rod is coupled to the actuator housing and extends therefrom. The anti-rotation is rod configured to at least selectively engage, and thereby prevent rotation of, the actuation member.

    Abstract translation: 致动器包括壳体组件，致动器轴，致动构件和防旋转杆。 致动器轴旋转地安装在壳体组件中，适于接收驱动扭矩，并且在接收到驱动转矩时被构造成旋转。 致动构件安装在致动器轴上，并且构造成响应于致动器轴的旋转而平移。 防旋转杆联接到致动器壳体并从其延伸。 防旋转杆被构造成至少选择性地接合，从而防止致动构件的旋转。

    ROTARY HYDRAULIC MOTOR DRIVEN HYBRID THRUST REVERSER ACTUATION SYSTEM WITH END-OF-STROKE SNUBBING
    4.
    发明申请
    ROTARY HYDRAULIC MOTOR DRIVEN HYBRID THRUST REVERSER ACTUATION SYSTEM WITH END-OF-STROKE SNUBBING 有权
    旋转液压马达驱动混合扭矩反转器启动系统

    公开(公告)号：US20150300294A1

    公开(公告)日：2015-10-22

    申请号：US14279016

    申请日：2014-05-15

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Kevin K. Chakkera ,  Ron Vaughan ,  Steve Abel

    IPC: F02K1/76

    CPC classification number: F02K1/763 ,  F01D17/26 ,  F02K1/72 ,  F02K1/74 ,  F02K1/76 ,  F02K1/766 ,  F05D2250/411 ,  F05D2260/406 ,  F05D2270/64 ,  F05D2270/66

    Abstract: An aircraft thrust reverser actuation system includes a plurality of actuator assemblies that are each configured, upon receipt of a drive torque, to move to a position. The rotary hydraulic motor is coupled to each of the actuator assemblies and is configured, upon receipt of hydraulic fluid, to rotate and supply the drive torque to each of the actuator assemblies. The control valve is in fluid communication with the rotary hydraulic motor and is configured, upon receipt of electrical current, to move to a valve position based on the magnitude of the received electrical current, to thereby control the direction and flow of hydraulic fluid to the hydraulic motor. The valve control is configured, upon receipt of thrust reverser commands, to supply the electrical current to the control valve and selectively vary the magnitude of the electrical current based on the positions of the actuator assemblies.

    Abstract translation: 飞机推力反向器致动系统包括多个致动器组件，每个致动器组件在接收到驱动转矩时被配置成移动到一个位置。 旋转液压马达联接到每个致动器组件，并且在接收到液压流体时被配置为旋转并将驱动扭矩提供给每个致动器组件。 控制阀与旋转液压马达流体连通，并且在接收到电流时被配置为基于所接收的电流的大小而移动到阀位置，从而控制液压流体的方向和流动 液压马达。 阀控制器被配置为在接收到推力反向器命令时将电流提供给控制阀，并且基于致动器组件的位置选择性地改变电流的大小。

    Variable area fan nozzle systems with improved drive couplings
    7.
    发明授权
    Variable area fan nozzle systems with improved drive couplings 有权
    可变区域风扇喷嘴系统，具有改进的驱动联轴器

    公开(公告)号：US09488130B2

    公开(公告)日：2016-11-08

    申请号：US14056526

    申请日：2013-10-17

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Kevin K. Chakkera ,  Ron Vaughan

    IPC: F02C1/00 ,  F02K1/72 ,  F16D3/06 ,  F02K1/80 ,  F02K1/76 ,  F02K3/06 ,  F02K1/06 ,  F16D3/205 ,  F02K1/08 ,  F02K1/09

    CPC classification number: F02K1/72 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K1/763 ,  F02K1/805 ,  F02K3/06 ,  F05D2260/4031 ,  F05D2270/44 ,  F05D2270/66 ,  F16D3/06 ,  F16D3/2052 ,  Y02T50/671

    Abstract: A VAFN system is provided for a fan case of an engine. The system includes a motor; a gearbox; an actuator; a nozzle; and a drive coupling extending between the gearbox and the actuator and configured to transmit the mechanical torque from the motor to the actuator. The drive coupling includes an external tube extending from a first one of the gearbox or the actuator, the external tube defining first and second slots extending in a longitudinal direction, and an internal tube extending from a second one of the gearbox or the actuator and at least partially extending within the external tube, the internal tube including a pin with first and second ends respectively positioned within the first and second slots such that the internal tube is configured to translate within the external tube and to be rotatably coupled to the external tube.

    Abstract translation: 为发动机的风扇箱提供VAFN系统。 该系统包括电机; 齿轮箱 执行机构 一个喷嘴; 以及驱动联轴器，其在所述齿轮箱和所述致动器之间延伸并且被配置为将所述机械扭矩从所述马达传递到所述致动器。 驱动联轴器包括从齿轮箱或致动器中的第一个延伸的外管，外管限定沿纵向方向延伸的第一和第二槽，以及从齿轮箱或致动器中的第二槽延伸的内管， 所述内管包括销，所述销的第一和第二端分别位于所述第一和第二槽内，使得所述内管构造成在所述外管内平移并且可旋转地联接到所述外管。

    AIRCRAFT ENGINE COWL DOOR MOVEMENT CONTROL SYSTEM AND METHOD
    8.
    发明申请
    AIRCRAFT ENGINE COWL DOOR MOVEMENT CONTROL SYSTEM AND METHOD 有权
    飞机发动机门运动控制系统及方法

    公开(公告)号：US20150078879A1

    公开(公告)日：2015-03-19

    申请号：US14063247

    申请日：2013-10-25

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Ron Vaughan ,  Leroy Allen Fizer ,  James Wawrzynek ,  Kevin K. Chakkera ,  Mohamed A. Salam ,  William Warr ,  Stephen Birn

    IPC: B64D29/08

    CPC classification number: B64D29/06 ,  F16H25/2204

    Abstract: A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation.

    Abstract translation: 提供一种系统和方法，用于控制在打开位置和关闭位置之间的飞机发动机罩门的移动。 该系统包括电动马达，至少一个致动器和电动制动器。 致动器联接到电动机并且可操作以在整流罩门在关闭位置和打开位置之间移动。 电动制动器联接到电动机和至少一个致动器，并且在通电时被配置为向电动机提供不阻止电动机旋转的单向阻力转矩负载。

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