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：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：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：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：US10464662B2

公开(公告)日：2019-11-05

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: B64C13/30 ,  B64C13/28 ,  B64C13/04 ,  B64C27/57 ,  B64C27/58 ,  F16F15/121 ,  B64C13/18

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：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.