公开(公告)号：US09650125B2

公开(公告)日：2017-05-16

申请号：US15231650

申请日：2016-08-08

Applicant: Merlin Technology, Inc.

Inventor： Carlos E. Golborne ,  Ray E. Debs ,  Mark Marvin ,  John E. Mercer

IPC: B64C13/04 ,  G05G9/047 ,  B64C13/22 ,  B64C27/04 ,  B64C13/18 ,  B64C27/56 ,  B64D43/00 ,  G01C23/00

CPC classification number: B64C13/22 ,  B64C13/04 ,  B64C13/18 ,  B64C27/04 ,  B64C27/56 ,  B64C27/57 ,  B64D43/00 ,  G01C23/00 ,  G01C23/005 ,  G05G9/047 ,  G05G2009/04774

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

公开(公告)号：US09150308B2

公开(公告)日：2015-10-06

申请号：US13763590

申请日：2013-02-08

Applicant: Merlin Technology, Inc.

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

IPC: H02K7/14 ,  B64C27/68 ,  B64C27/59 ,  B64C13/04 ,  B64C13/30 ,  B64C27/57 ,  B64C27/58

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。

公开(公告)号：US20140027565A1

公开(公告)日：2014-01-30

申请号：US13763582

申请日：2013-02-08

Applicant: Merlin Technology, Inc.

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

IPC: B64C27/57

CPC classification number: B64C27/57 ,  B64C13/0421 ,  B64C13/044 ,  B64C13/341 ,  B64C27/58 ,  G05D1/0858

Abstract: An autopilot system includes an actuator arrangement that receives control signals to influence the flight of the helicopter in a selected one of a plurality of different flight modes. A control stick input arrangement allows flight mode selection and control with no more than a particular one of the pilot's hands in the engaged position on the stick and without moving the hand away from the engaged position. A slaved gyro output signal is based on no more than the set of sensor outputs used by the autopilot such that an autopilot display presents autopilot flight mode information while displaying a slaved gyro output. The autopilot provides for pilot selection of one of a subset of the plurality of flight modes which is customized based on a current flight status of the helicopter. An automatic autorotation mode is provided.

Abstract translation: 自动驾驶仪系统包括致动器装置，该致动器装置接收控制信号以影响直升机在多种不同飞行模式中所选择的一种中的飞行。 控制杆输入装置允许飞行模式的选择和控制，不超过驾驶员手中特定的一只手在杆上的接合位置，而不用将手从接合位置移开。 从动陀螺仪输出信号基于自动驾驶仪使用的传感器输出集合，使得自动驾驶仪显示器显示自动驾驶飞行模式信息，同时显示从属陀螺仪输出。 自动驾驶仪提供了基于直升机的当前飞行状态来定制的多个飞行模式的子集中的一个的飞行员选择。 提供自动自动转换模式。

公开(公告)号：US11820498B2

公开(公告)日：2023-11-21

申请号：US17176864

申请日：2021-02-16

Applicant: Merlin Technology, Inc.

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

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

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.

公开(公告)号：US20210179264A1

公开(公告)日：2021-06-17

申请号：US17176864

申请日：2021-02-16

Applicant: Merlin Technology, Inc.

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

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

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.

公开(公告)号：US10919622B2

公开(公告)日：2021-02-16

申请号：US15926972

申请日：2018-03-20

Applicant: Merlin Technology, Inc.

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

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

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.

公开(公告)号：US20180346110A1

公开(公告)日：2018-12-06

申请号：US16109170

申请日：2018-08-22

Applicant: Merlin Technology Inc.

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

IPC: B64C27/68 ,  F16F15/121 ,  B64C13/18 ,  B64C27/58 ,  B64C27/57 ,  B64C13/04 ,  B64C27/59 ,  B64C13/30

CPC classification number: B64C27/58 ,  B64C13/0421 ,  B64C13/18 ,  B64C13/343 ,  B64C27/57 ,  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.

公开(公告)号：US20170129599A1

公开(公告)日：2017-05-11

申请号：US15415469

申请日：2017-01-25

Applicant: Merlin Technology Inc.

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

IPC: B64C27/68 ,  B64C27/57 ,  B64C13/30 ,  B64C13/18

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.

公开(公告)号：US09586681B2

公开(公告)日：2017-03-07

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 ,  B64C27/68 ,  B64C13/04 ,  B64C13/30 ,  B64C27/57 ,  B64C27/58 ,  F16F15/121

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。

公开(公告)号：US20170008624A1

公开(公告)日：2017-01-12

申请号：US15158521

申请日：2016-05-18

Applicant: Merlin Technology, Inc.

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

IPC: B64C27/57 ,  B64C27/59 ,  B64C27/04 ,  B64C27/00

CPC classification number: B64C27/57 ,  B64C27/006 ,  B64C27/56 ,  B64C27/58 ,  B64C27/59

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.

Abstract translation: 紧急集体执行器包括致动器马达以产生致动力和致动器连杆，其直接接合摩擦控制杆，所述摩擦控制杆枢转地支撑在直升机的集体杆上，以将致动力直接施加到摩擦控制杆，使得致动 力最初脱离摩擦控制，然后将可调节距减小到最小集体俯仰位置。 致动器可包括离合器，其滑动以允许飞行员克服致动力，并且响应于飞行员的摩擦控制的接合滑动，但是否则离合器与马达轴共同旋转以将可调俯仰偏压朝向 最低集体职位。