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    Compact linear hydraulic actuator
    2.
    发明授权
    Compact linear hydraulic actuator 有权

    公开(公告)号：US10239610B2

    公开(公告)日：2019-03-26

    申请号：US15062375

    申请日：2016-03-07

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Carlos A. Fenny ,  Carl T. Elving ,  Rodney M. Cahoon ,  Charles Eric Covington

    IPC: B64C27/64 ,  B64C27/605 ,  F15B15/14

    Abstract: In some embodiments, an actuator includes a chamber, a piston disposed within the chamber, and a tube. The chamber has a first port and a second port. The piston comprises a first surface, a second surface, and an elongated conduit coupling the first surface to the second surface. The first surface is disposed between the first port and the second port. The second surface is offset from the first surface. The tube is disposed at least partially within the elongated conduit of the piston. The tube comprises a third port disposed within the elongated conduit of the piston and a fourth port disposed outside of the elongated conduit of the piston.

    Tiltrotor control system with two rise/fall actuators
    4.
    发明授权
    Tiltrotor control system with two rise/fall actuators 有权
    具有两个上升/下降执行器的倾翻机控制系统

    公开(公告)号：US09567070B2

    公开(公告)日：2017-02-14

    申请号：US13835705

    申请日：2013-03-15

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Ken Shundo ,  Carlos A. Fenny ,  Frank B. Stamps

    IPC: B64C27/10 ,  B64C29/00 ,  B64C11/32 ,  B64C27/605

    CPC classification number: B64C29/0033 ,  B64C11/32 ,  B64C27/605

    Abstract: A rotor system for rotor aircraft comprises a rotor hub comprising a plurality of rotor blades, a rotatable rotor mast coupled to the rotor hub, a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, and a swashplate actuator system. The rotatable ring is configured to rotate with the rotor mast, and the non-rotating ring is configured to engage and guide the rotatable ring. The pitch links are configured to control the pitch angle of each rotor blade. The swashplate actuator system consists of: a first actuator and a second actuator, where the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring.

    Abstract translation: 用于转子飞行器的转子系统包括转子毂，该转子毂包括多个转子叶片，连接到转子毂的可旋转转子柱塞，包括与可旋转环接合的非旋转环的斜盘组件，多个螺距连杆， 可旋转环到多个转子叶片，以及斜盘致动器系统。 可旋转环被构造成与转子桅杆一起旋转，并且非旋转环被构造成接合和引导可旋转环。 俯仰连杆构造成控制每个转子叶片的俯仰角。 斜盘致动器系统包括：第一致动器和第二致动器，其中第一致动器和第二致动器机械地联接到固定表面和非旋转环。

    Magnetorheological Haptic Trim Actuator
    5.
    发明申请
    Magnetorheological Haptic Trim Actuator 有权
    磁流变触发修整执行机构

    公开(公告)号：US20160221672A1

    公开(公告)日：2016-08-04

    申请号：US14609905

    申请日：2015-01-30

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Geoffrey C. Latham ,  Carlos A. Fenny ,  Jean-Sébastian Plante ,  Brady Atkins ,  Guifré Julio ,  Marc Denninger ,  Charles Eric Covington ,  Paul Wilson

    IPC: B64C27/64 ,  B64C27/68 ,  B64C27/56

    CPC classification number: B64C27/68 ,  B64C27/56 ,  B64D43/00

    Abstract: According to one embodiment, a trim actuator for a pilot input device includes a driven member and a driving member configured to receive mechanical energy from a power source. A magnetorheological (MR) fluid is disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member. An output member configured to be coupled between the driven member and the pilot input device. A magnetic circuit configured to deliver a magnetic field towards the MR fluid. The magnetic circuit is configured to control movement of the pilot input device by varying the strength of the magnetic field delivered towards the first MR fluid.

    Abstract translation: 根据一个实施例，用于先导输入装置的修整致动器包括从动构件和构造成从动力源接收机械能的驱动构件。 磁流变（MR）流体设置在驱动构件和从动构件之间，并且构造成将可变量的机械能从驱动构件传递到从动构件。 输出构件，被配置为联接在从动构件和导向输入装置之间。 磁路，被配置为向MR流体传送磁场。 磁路被配置为通过改变朝向第一MR流体传送的磁场的强度来控制先导输入装置的运动。

    FOLDING OF ROTORCRAFT ROTOR BLADES
    6.
    发明申请
    FOLDING OF ROTORCRAFT ROTOR BLADES 有权
    转子转子叶片的折叠

    公开(公告)号：US20150274290A1

    公开(公告)日：2015-10-01

    申请号：US13949698

    申请日：2013-07-24

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Carlos A. Fenny ,  Troy Schank ,  Frank B. Stamps

    IPC: B64C27/50 ,  B64C27/52

    CPC classification number: B64C27/30 ,  B64C11/28 ,  B64C27/32 ,  B64C27/41 ,  B64C27/50 ,  B64C27/52 ,  B64C27/605 ,  B64C27/615 ,  B64C29/0033

    Abstract: According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.

    Abstract translation: 根据一个实施例，转子叶片旋转系统包括轮毂，转子叶片，其与轮毂机械连通并可围绕旋转轴线旋转，斜盘，俯仰杆和致动器。 旋转斜盘包括旋转部分和非旋转部分。 节距连杆联接到旋转斜盘的旋转部分并且与转子叶片机械连通。 致动器联接到旋转斜盘的非旋转部分并且可操作以将斜盘从第一位置重新定位到第二位置，使得俯仰杆将转子叶片从展开位置枢转到折叠位置。

    Rotorcraft Anti-torque Control System
    8.
    发明申请
    Rotorcraft Anti-torque Control System 审中-公开
    转子防扭矩控制系统

    公开(公告)号：US20140374534A1

    公开(公告)日：2014-12-25

    申请号：US13925008

    申请日：2013-06-24

    Applicant: Bell Helicopter Textron Inc.

    Inventor： James M. McCollough ,  Carlos A. Fenny

    IPC: B64C27/82

    CPC classification number: B64C27/82 ,  B64C2027/8254 ,  B64C2027/8272

    Abstract: According to one embodiment, a rotorcraft includes a main rotor system, an anti-torque rotor system, an anti-torque rudder system, and an anti-torque control system. The anti-torque rudder system includes at least one rudder surface operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade. The anti-torque control system is operable to receive a request to change an amount of anti-torque force applied to the body, compare a rotorcraft performance parameter to a threshold value, instruct one of the anti-torque rotor system or the anti-torque rudder system to change the amount of the first force if the rotorcraft performance parameter is less than the threshold value, and, if the rotorcraft performance parameter is greater than the threshold value, instruct the other of the anti-torque rotor system or the anti-torque rudder system to change the amount of the second force.

    Abstract translation: 根据一个实施例，旋翼航空器包括主转子系统，抗扭矩转子系统，抗扭矩舵系统和抗扭矩控制系统。 防扭矩舵系统包括至少一个方向舵表面，其可操作以在所述主体上沿所述至少一个主转子叶片的旋转方向提供第二力。 抗扭矩控制系统可操作以接收改变施加到车身的抗扭矩力的量的请求，将旋翼航空器的性能参数与阈值进行比较，指示抗扭矩转子系统或抗扭矩 方向舵系统，如果旋翼航空器的性能参数小于阈值，则改变第一力的量，并且如果旋翼航空器的性能参数大于阈值，则指示另一个抗扭矩转子系统或抗扭矩转子系统， 扭矩舵系统改变第二力的量。

    Direct-Drive Control of Aircraft Stability Augmentation
    9.
    发明申请
    Direct-Drive Control of Aircraft Stability Augmentation 有权
    直升机控制飞机稳定性增强

    公开(公告)号：US20140110532A1

    公开(公告)日：2014-04-24

    申请号：US13655778

    申请日：2012-10-19

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Charles E. Covington ,  Carlos A. Fenny ,  Brady G. Atkins

    IPC: B64C27/59

    CPC classification number: B64C27/59 ,  B64C27/605 ,  B64C2027/004 ,  Y10T74/18056

    Abstract: According to one embodiment, a stability augmentation system includes a master linkage, a stability augmentation motor, and three linkages. A first linkage is coupled to the master linkage and operable to receive movements representative of pilot commands from a pilot command system. A second linkage is coupled between the stability augmentation motor and the master linkage and operable to receive movements representative of augmentation commands from the stability augmentation motor. A third linkage is coupled to the master linkage and operable to transmit movements representative of blade position commands to a blade control system in response to the movements representative of pilot commands and the movements representative of augmentation commands.

    Abstract translation: 根据一个实施例，稳定性增强系统包括主联动装置，稳定性增加电动机和三个联动装置。 第一联动装置耦合到主联动装置并且可操作以从导向指令系统接收代表导向指令的运动。 第二联动装置耦合在稳定性增强电动机和主联动装置之间，并且可操作以从稳定性增强电动机接收代表增强指令的运动。 第三联动装置联接到主联动装置并且可操作以响应于代表导向命令的运动和代表增加命令的运动而将代表刀片位置命令的运动传送到刀片控制系统。

    Tail rotor actuation system
    10.
    发明授权
    Tail rotor actuation system 有权

    公开(公告)号：US10023304B2

    公开(公告)日：2018-07-17

    申请号：US14286197

    申请日：2014-05-23

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Corey Dickman ,  Carlos A. Fenny ,  David Schultz

    IPC: B64C27/12 ,  B64C13/50 ,  B64C27/82 ,  B64C27/14

    Abstract: In some embodiments, an actuation system includes a an actuator assembly, a yoke, and a control rod. The actuator assembly comprises a first actuator. The first actuator is configured to extend in a first direction and retract in a second direction opposite of the first direction. The yoke is coupled to the first actuator at a first actuator end proximate to the first direction. The control rod is coupled to the yoke at a first control rod end and extends in the second direction past the actuator assembly to a second end in mechanical communication with an output device.

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