公开(公告)号：US09272780B2

公开(公告)日：2016-03-01

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 ,  B64C13/18 ,  B64C13/42 ,  G05D1/08

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。

公开(公告)号：US11591078B2

公开(公告)日：2023-02-28

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.

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.

公开(公告)号：US09758244B2

公开(公告)日：2017-09-12

申请号：US15015689

申请日：2016-02-04

Applicant: Merlin Technology, Inc.

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

IPC: B64C27/57 ,  B64C27/64 ,  B64C27/68 ,  G05D1/08 ,  B64C27/56 ,  G05D1/10 ,  B64C13/18 ,  B64C13/42 ,  B64C27/59 ,  G05D1/00

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.

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.

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。

公开(公告)号：US20190352003A1

公开(公告)日：2019-11-21

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

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.

公开(公告)号：US10351231B2

公开(公告)日：2019-07-16

申请号：US15687454

申请日：2017-08-26

Applicant: Merlin Technology, Inc.

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

IPC: B64C27/57 ,  B64C13/18 ,  B64C13/42 ,  B64C27/56 ,  B64C27/59 ,  B64C27/64 ,  B64C27/68 ,  G05D1/00 ,  G05D1/08 ,  G05D1/10

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.

公开(公告)号：US20180093763A1

公开(公告)日：2018-04-05

申请号：US15687454

申请日：2017-08-26

Applicant: Merlin Technology, Inc.

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

IPC: B64C27/57 ,  G05D1/00 ,  G05D1/08 ,  B64C27/68 ,  B64C27/64 ,  B64C27/59 ,  B64C13/42 ,  B64C13/18 ,  G05D1/10 ,  B64C27/56

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.

公开(公告)号：US20160152330A1

公开(公告)日：2016-06-02

申请号：US15015689

申请日：2016-02-04

Applicant: Merlin Technology, Inc.

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

IPC: B64C27/57 ,  B64C27/68 ,  B64C27/64 ,  G05D1/08

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。