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    ADVANCED EMERGENCY COLLECTIVE ACTUATOR WITH FRICTION PULL-OFF AND METHOD FOR A HELICOPTER
    1.
    发明公开
    ADVANCED EMERGENCY COLLECTIVE ACTUATOR WITH FRICTION PULL-OFF AND METHOD FOR A HELICOPTER 审中-公开

    公开(公告)号：US20240253777A1

    公开(公告)日：2024-08-01

    申请号：US18379159

    申请日：2023-10-12

    Applicant: Merlin Technology, Inc.

    Inventor： Mark Marvin ,  John E. Mercer ,  Derek Velter

    IPC: B64C27/57 ,  B64C27/00 ,  B64C27/56

    CPC classification number: B64C27/57 ,  B64C27/006 ,  B64C27/56

    Abstract: An emergency collective actuator includes an actuator motor to produce an actuation force and an actuator linkage that directly engages a friction control lever that is pivotally supported on the collective stick of a helicopter to apply the actuation force directly to the friction control lever such that the actuation force initially disengages the friction control and then reduces the adjustable pitch toward a minimum collective pitch position. The actuator can include a clutch that slips to allow the pilot to overcome the actuation force and that slips responsive to an engagement of the friction control by the pilot, but otherwise the clutch co-rotates with the motor shaft to bias the adjustable pitch toward a minimum collective pitch position.

    ROTORCRAFT AUTOPILOT AND METHODS
    3.
    发明申请
    ROTORCRAFT AUTOPILOT AND METHODS 有权

    公开(公告)号：US20210245871A1

    公开(公告)日：2021-08-12

    申请号：US17159156

    申请日：2021-01-27

    Applicant: Merlin Technology, Inc.

    Inventor： John E. Mercer ,  Nicholas Albion ,  Mark Bartel ,  Marc Feifel ,  Mark Marvin

    IPC: B64C27/57 ,  B64C27/56 ,  G05D1/10 ,  B64C13/18 ,  G05D1/08 ,  G05D1/00 ,  B64C13/28 ,  B64C13/04 ,  B64C27/58 ,  B64C27/59 ,  B64C27/64 ,  B64C27/68

    Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

    ROTORCRAFT AUTOPILOT SYSTEM, COMPONENTS AND METHODS
    4.
    发明申请
    ROTORCRAFT AUTOPILOT SYSTEM, COMPONENTS AND METHODS 有权
    旋转自动系统，组件和方法

    公开(公告)号：US20160023758A1

    公开(公告)日：2016-01-28

    申请号：US14858080

    申请日：2015-09-18

    Applicant: Merlin Technology Inc.

    Inventor： John E. Mercer ,  Marc Feifel ,  Mark Marvin ,  Nicolas Albion

    IPC: B64C27/59 ,  B64C27/57 ,  F16F15/121 ,  B64C27/68

    CPC classification number: B64C27/68 ,  B64C13/04 ,  B64C13/18 ,  B64C13/30 ,  B64C27/57 ,  B64C27/58 ,  B64C27/59 ,  F16F15/121 ,  Y02T50/44

    Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

    Abstract translation: 自动驾驶执行器包括第一和第二电动机，每个电动机包括可旋转的电动机输出轴，使得电动机中的一个或两个可以驱动致动器输出轴。 自动驾驶仪主机壳体可拆卸地安装在靠近循环控制的直升机上，并且通常容纳自动驾驶执行器以及主要的自动驾驶仪电子装置。 循环式隔振器由致动器轴可拆卸地支撑，用于共同旋转并且耦合到循环控制器，以在致动器轴处衰减循环振动频率，同时致动器轴的低于谐振频率的转速耦合到循环控制。 力限制连杆包括第一和第二端以及两者之间的可变长度。 当施加小于放开力的力时，力限制连杆具有松弛的长度，并且当施加的力超过转动力以允许引导超驰时，可变长度改变。

    ROTORCRAFT AUTOPILOT AND METHODS
    5.
    发明申请
    ROTORCRAFT AUTOPILOT AND METHODS 有权
    旋转自动机和方法

    公开(公告)号：US20140027564A1

    公开(公告)日：2014-01-30

    申请号：US13763574

    申请日：2013-02-08

    Applicant: Merlin Technology, Inc.

    Inventor： John E. Mercer ,  Nicolas Albion ,  Mark Bartel ,  Marc Feifel ,  Mark Marvin

    IPC: B64C27/57 ,  B64C27/59 ,  B64C27/64 ,  B64C27/68

    CPC classification number: B64C27/57 ,  B64C13/18 ,  B64C13/42 ,  B64C27/56 ,  B64C27/59 ,  B64C27/64 ,  B64C27/68 ,  G05D1/0077 ,  G05D1/0816 ,  G05D1/0858 ,  G05D1/102 ,  Y02T50/44

    Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

    Abstract translation: 直升机自动驾驶系统包括用于直升机飞行的姿态保持的内循环，包括施加到内循环的给定水平的冗余。 外部环路被配置为提供关于直升机的飞行的导航功能，其包括与内部循环不同的冗余级别。 致动器在联动装置上提供制动力，用于在停电期间稳定直升机的飞行。 致动器是机电的并且接收电驱动信号以提供直升机的自动飞行控制，而不需要直升机中的液压辅助系统。 自动驾驶仪可以在液压辅助系统的故障模式下操作直升机。 使用相关的传感器输入描述了多个飞行模式，包括基于速率和真实姿态模式。

    Rotorcraft autopilot and methods
    6.
    发明授权
    Rotorcraft autopilot and methods 有权

    公开(公告)号：US10926872B2

    公开(公告)日：2021-02-23

    申请号：US16510897

    申请日：2019-07-13

    Applicant: Merlin Technology, Inc.

    Inventor： John E. Mercer ,  Nicholas Albion ,  Mark Bartel ,  Marc Feifel ,  Mark Marvin

    IPC: B64C27/57 ,  B64C27/56 ,  G05D1/10 ,  B64C13/18 ,  G05D1/08 ,  G05D1/00 ,  B64C27/59 ,  B64C27/64 ,  B64C27/68

    Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

    REMOVABLY ATTACHABLE GPS MODULE FOR A PORTABLE LOCATOR
    7.
    发明申请
    REMOVABLY ATTACHABLE GPS MODULE FOR A PORTABLE LOCATOR 审中-公开

    公开(公告)号：US20180364362A1

    公开(公告)日：2018-12-20

    申请号：US16114189

    申请日：2018-08-27

    Applicant: Merlin Technology, Inc.

    Inventor： Mark Marvin ,  Brian Kelly

    IPC: G01S19/14 ,  H01Q1/22 ,  G08B5/36 ,  G01S19/35

    Abstract: A portable locator includes a locator housing having a display head that supports a display. A GPS module includes a frame and an antenna arm extending from a side margin of the frame. The frame defines a display aperture such that the frame is removably installable on the display head of the portable locator with the display visible through the display aperture. An electrical interface provides for electrical communication with the portable locator with the frame removably installed thereon.

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