公开(公告)号：US20180093762A1

公开(公告)日：2018-04-05

申请号：US15646680

申请日：2017-07-11

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Shyhpyng Jack Shue ,  John James Corrigan ,  Eric Thomas Bird ,  Tommie Lynn Wood ,  Alan Carl Ewing

IPC: B64C27/54 ,  B64C19/00 ,  G05B19/042 ,  G05B23/02 ,  G05D1/00 ,  G05D1/08

CPC classification number: B64C27/54 ,  B64C19/00 ,  G05B19/0428 ,  G05B23/0289 ,  G05B2219/24192 ,  G05B2219/25069 ,  G05D1/0077 ,  G05D1/0858

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.

公开(公告)号：US09701404B2

公开(公告)日：2017-07-11

申请号：US14321443

申请日：2014-07-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Shyhpyng Jack Shue ,  John James Corrigan ,  Eric Thomas Bird ,  Tommie Lynn Wood ,  Alan Carl Ewing

IPC: B64C11/00 ,  B64C27/54 ,  G05D1/00 ,  G05D1/08 ,  G05B19/042 ,  G05B23/02 ,  B64C19/00

CPC classification number: B64C27/54 ,  B64C19/00 ,  G05B19/0428 ,  G05B23/0289 ,  G05B2219/24192 ,  G05B2219/25069 ,  G05D1/0077 ,  G05D1/0858

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.

公开(公告)号：US10183743B2

公开(公告)日：2019-01-22

申请号：US15646680

申请日：2017-07-11

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Shyhpyng Jack Shue ,  John James Corrigan ,  Eric Thomas Bird ,  Tommie Lynn Wood ,  Alan Carl Ewing

IPC: B64C27/54 ,  G05D1/00 ,  G05D1/08 ,  G05B19/042 ,  G05B23/02 ,  B64C19/00

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.