Patents by Inventor Shyhpyng Jack Shue

Shyhpyng Jack Shue has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20140316615
    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.
    Type: Application
    Filed: July 1, 2014
    Publication date: October 23, 2014
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
  • Patent number: 8763950
    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.
    Type: Grant
    Filed: September 3, 2013
    Date of Patent: July 1, 2014
    Assignee: Texron Innovations Inc.
    Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
  • Patent number: 8682505
    Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture.
    Type: Grant
    Filed: December 11, 2012
    Date of Patent: March 25, 2014
    Assignee: Textron Innovations Inc.
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
  • Publication number: 20140005862
    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.
    Type: Application
    Filed: September 3, 2013
    Publication date: January 2, 2014
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
  • Publication number: 20130325221
    Abstract: An air/ground contact logic management system for use with fly-by-wire control systems in an aircraft. The system includes a first sensor configured to provide an output signal to determine when the aircraft is in a transition region. A logic management system is in communication with the first sensor and is configured to receive and process the output signal and classify a mode of the aircraft. A controller receives signal data from the logic management system and communicates with a control axis actuator to regulate a level of control authority provided to a pilot. The control authority is individually regulated within each integrator as a result of the individual landing gear states.
    Type: Application
    Filed: June 5, 2012
    Publication date: December 5, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: Shyhpyng Jack Shue
  • Publication number: 20130274963
    Abstract: A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition.
    Type: Application
    Filed: June 25, 2013
    Publication date: October 17, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Shyhpyng Jack Shue, John J. Schillings
  • Publication number: 20130261853
    Abstract: A system includes a plurality of actuators and a management system operably associated with the plurality electronic and mechanical devices. The management architecture includes interfaces configured to the entire electronics and mechanics to provide a parameter to a computer. The computer includes a control and management architecture using modular finite state flow designs configured to analyze the parameter. The computer with a plurality of finite state machines can conduct a plurality of control laws operably associated with one or more actuators for finite functions of mobility. The method includes matching the parameter with the finite state machine and controlling the actuator via control law operably associated with finite state machine. The method can therefore be achieved either manually, semi-autonomously and autonomously with seamless and switchless control using a central control computer with integration of electronic and mechanic sensors and devices.
    Type: Application
    Filed: June 11, 2013
    Publication date: October 3, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Shyhpyng Jack Shue, John J. Shillings
  • Patent number: 8523102
    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 and 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. A sensor management tool is provided for 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.
    Type: Grant
    Filed: October 5, 2009
    Date of Patent: September 3, 2013
    Assignee: Textron Innovations Inc.
    Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
  • Patent number: 8473124
    Abstract: A flight control system is configured for controlling the flight of an aircraft utilizing a three control loop design to robustly increase system performance. An inner loop comprises an improved linear quadratic regulator (LQR) search method, and an outer loop comprises a classic feedback summary gain design. A third loop comprises a steady state trim search method.
    Type: Grant
    Filed: November 8, 2005
    Date of Patent: June 25, 2013
    Assignee: Textron Innovations Inc.
    Inventors: Shyhpyng Jack Shue, John J. Shillings
  • Publication number: 20130138270
    Abstract: A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope; engaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; and engaging a position hold with a control law position hold architecture as the aircraft enters the second flight envelope.
    Type: Application
    Filed: July 15, 2011
    Publication date: May 30, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
  • Publication number: 20130090788
    Abstract: A flight control system and method for controlling full envelope banked turns of an aircraft, the flight control system including one or more of a control law architectures having one or more control laws adapted for controlling the flight of an aircraft for full envelope banked turns.
    Type: Application
    Filed: March 29, 2011
    Publication date: April 11, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill, Nicholas Dean Lappos
  • Publication number: 20130060406
    Abstract: A flight control system and method for controlling the vertical flight path of an aircraft, the flight control system includes a stable decoupled model having a decoupled lateral equation of motion and a decoupled longitudinal equation of motion and a feedback command loop operably associated with the stable decoupled model. The feedback command loop includes a vertical flight path angle control law; an altitude control law; and a vertical speed control law.
    Type: Application
    Filed: January 14, 2011
    Publication date: March 7, 2013
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
  • Patent number: 8332082
    Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed.
    Type: Grant
    Filed: March 30, 2011
    Date of Patent: December 11, 2012
    Assignee: Textron Innovations Inc.
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
  • Publication number: 20120253558
    Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed.
    Type: Application
    Filed: March 30, 2011
    Publication date: October 4, 2012
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
  • Patent number: 8170730
    Abstract: A flight control system is configured for controlling the flight of an aircraft through windshear conditions. The system has means for measuring values of selected flight performance states of the aircraft and a control system for operating flight control devices on the aircraft. A windshear detection system located on the aircraft uses at least some of the measured values of the selected flight performance states to calculate a gust average during flight for comparison to pre-determined values in a table for determining whether windshear conditions exist. The control system then operates at least some of the flight control devices in response to an output of the windshear detection system.
    Type: Grant
    Filed: July 28, 2011
    Date of Patent: May 1, 2012
    Assignee: Textron Innovations Inc.
    Inventor: Shyhpyng Jack Shue
  • Publication number: 20110282523
    Abstract: A flight control system is configured for controlling the flight of an aircraft through windshear conditions. The system has means for measuring values of selected flight performance states of the aircraft and a control system for operating flight control devices on the aircraft. A windshear detection system located on the aircraft uses at least some of the measured values of the selected flight performance states to calculate a gust average during flight for comparison to pre-determined values in a table for determining whether windshear conditions exist. The control system then operates at least some of the flight control devices in response to an output of the windshear detection system.
    Type: Application
    Filed: July 28, 2011
    Publication date: November 17, 2011
    Inventor: Shyhpyng Jack Shue
  • Patent number: 8000847
    Abstract: A flight control system is configured for controlling the flight of an aircraft through windshear conditions. The system has means for measuring values of selected flight performance states of the aircraft and a control system for operating flight control devices on the aircraft. A windshear detection system located on the aircraft uses at least some of the measured values of the selected flight performance states to calculate a gust average during flight for comparison to pre-determined values in a table for determining whether windshear conditions exist. The control system then operates at least some of the flight control devices in response to an output of the windshear detection system.
    Type: Grant
    Filed: October 11, 2005
    Date of Patent: August 16, 2011
    Assignee: Textron Innovations Inc.
    Inventor: Shyhpyng Jack Shue
  • Publication number: 20110180656
    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 and 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. A sensor management tool is provided for 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.
    Type: Application
    Filed: October 5, 2009
    Publication date: July 28, 2011
    Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing