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1. 发明申请

US20210245871A1 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
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Nicholas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C27/56 , G05D1/10 , B64C13/18 , G05D1/08 , G05D1/00 , B64C13/28 , B64C13/04 , B64C27/58 , B64C27/59 , B64C27/64 , B64C27/68
摘要： 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.

2. 发明申请

US20160023758A1 ROTORCRAFT AUTOPILOT SYSTEM, COMPONENTS AND METHODS 有权
标题翻译：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
申请人： Merlin Technology Inc.
发明人： John E. Mercer , Marc Feifel , Mark Marvin , Nicolas Albion
IPC分类号： B64C27/59 , B64C27/57 , F16F15/121 , B64C27/68
CPC分类号： B64C27/68 , B64C13/04 , B64C13/18 , B64C13/30 , B64C27/57 , B64C27/58 , B64C27/59 , F16F15/121 , Y02T50/44
摘要： 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.
摘要翻译：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。

3. 发明申请

US20140027564A1 ROTORCRAFT AUTOPILOT AND METHODS 有权
标题翻译：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
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Nicolas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C27/59 , B64C27/64 , B64C27/68
CPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/0077 , G05D1/0816 , G05D1/0858 , G05D1/102 , Y02T50/44
摘要： 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.
摘要翻译：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。

4. 发明授权

US11591078B2 Rotorcraft autopilot and methods 有权
公开(公告)号：US11591078B2
公开(公告)日：2023-02-28
申请号：US17159156
申请日：2021-01-27
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Nicholas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C27/56 , G05D1/10 , B64C13/18 , G05D1/08 , G05D1/00 , B64C13/28 , B64C13/04 , B64C27/58 , B64C27/59 , B64C27/64 , B64C27/68
摘要： 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.

5. 发明授权

US10464662B2 Rotorcraft autopilot system, components and methods 有权
公开(公告)号：US10464662B2
公开(公告)日：2019-11-05
申请号：US16109170
申请日：2018-08-22
申请人： Merlin Technology Inc.
发明人： John E. Mercer , Marc Feifel , Mark Marvin , Nicholas Albion
IPC分类号： B64C13/30 , B64C13/28 , B64C13/04 , B64C27/57 , B64C27/58 , F16F15/121 , B64C13/18
摘要： 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.

6. 发明申请

US20140027566A1 ROTORCRAFT AUTOPILOT SYSTEM, COMPONENTS AND METHODS 有权
标题翻译：旋转自动系统，组件和方法
公开(公告)号：US20140027566A1
公开(公告)日：2014-01-30
申请号：US13763590
申请日：2013-02-08
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Marc Feifel , Mark Marvin , Nicolas Albion
IPC分类号： B64C27/68 , B64C27/59
CPC分类号： B64C27/68 , B64C13/04 , B64C13/18 , B64C13/30 , B64C27/57 , B64C27/58 , B64C27/59 , F16F15/121 , Y02T50/44
摘要： 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.
摘要翻译：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。

7. 发明授权

US10926872B2 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
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Nicholas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C27/56 , G05D1/10 , B64C13/18 , G05D1/08 , G05D1/00 , B64C27/59 , B64C27/64 , B64C27/68
摘要： 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.

8. 发明授权

US09758244B2 Rotorcraft autopilot and methods 有权
公开(公告)号：US09758244B2
公开(公告)日：2017-09-12
申请号：US15015689
申请日：2016-02-04
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Nicolas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C27/64 , B64C27/68 , G05D1/08 , B64C27/56 , G05D1/10 , B64C13/18 , B64C13/42 , B64C27/59 , G05D1/00
CPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/0077 , G05D1/0816 , G05D1/0858 , G05D1/102 , Y02T50/44
摘要： 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.

9. 发明授权

US09150308B2 Rotorcraft autopilot system, components and methods 有权
标题翻译： Rotorcraft自动驾驶仪系统，组件和方法
公开(公告)号：US09150308B2
公开(公告)日：2015-10-06
申请号：US13763590
申请日：2013-02-08
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Marc Feifel , Mark Marvin , Nicolas Albion
IPC分类号： H02K7/14 , B64C27/68 , B64C27/59 , B64C13/04 , B64C13/30 , B64C27/57 , B64C27/58
CPC分类号： B64C27/68 , B64C13/04 , B64C13/18 , B64C13/30 , B64C27/57 , B64C27/58 , B64C27/59 , F16F15/121 , Y02T50/44
摘要： 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.
摘要翻译：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。

10. 发明申请

US20140027565A1 ROTORCRAFT ADVANCED AUTOPILOT CONTROL ARRANGEMENT AND METHODS 审中-公开
标题翻译：旋转高级自动控制装置和方法
公开(公告)号：US20140027565A1
公开(公告)日：2014-01-30
申请号：US13763582
申请日：2013-02-08
申请人： Merlin Technology, Inc.
发明人： Mark Marvin , Marc Feifel , Nicolas Albion , John E. Mercer
IPC分类号： B64C27/57
CPC分类号： B64C27/57 , B64C13/0421 , B64C13/044 , B64C13/341 , B64C27/58 , G05D1/0858
摘要： 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.
摘要翻译：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。

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