Patents by Inventor Joseph G. Irwin, III

Joseph G. Irwin, III 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).

  • Patent number: 11016506
    Abstract: A control circuitry includes a first filter configured to filter a gravity compensated longitudinal acceleration of an aircraft to generate a filtered gravity compensated longitudinal acceleration. The propulsor trim control circuitry also includes a second filter configured to generate a filtered speed of the aircraft based on a speed of the aircraft. The propulsor trim control circuitry includes intermediary circuitry configured to generate a filtered longitudinal control effector error based on the filtered gravity compensated longitudinal acceleration and the speed. The propulsor trim control circuitry also includes a third filter configured to generate a filtered longitudinal thrust effector command value based on a longitudinal thrust effector command value.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: May 25, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Patent number: 10935985
    Abstract: A control circuitry includes a propulsor trim prediction circuitry and an output circuitry. The propulsor trim prediction circuitry is configured to generate a predicted proprotor nacelle trim value based on an aircraft velocity and a pitch attitude deviation from a reference. The output circuitry is configured to output a proprotor nacelle command based on the predicted proprotor nacelle trim value. The proprotor nacelle command is configured to cause an adjustment in a nacelle angle of a proprotor of an aircraft.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: March 2, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Patent number: 10877487
    Abstract: A control circuitry includes a propulsor trim prediction circuitry configured to generate a predicted propulsor collective blade pitch trim value for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference. The control circuitry further includes an output circuitry configured to output a propulsor collective blade pitch angle command based on the predicted propulsor collective blade pitch trim value. The propulsor collective blade pitch angle command is configured to cause an adjustment in a blade pitch angle of a propulsor of the aircraft. Additionally or alternatively, the control circuitry includes a pitch attitude trim prediction circuitry configured to generate a predicted pitch attitude trim value. The output circuitry is configured to output an aircraft pitch attitude trim command, configured to cause an adjustment in a pitch angle of the aircraft, based on the predicted pitch attitude trim value.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: December 29, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Patent number: 10747235
    Abstract: A control circuitry includes a first filter configured to generate a filtered velocity based on a component of a vertical velocity of an aircraft. The pitch trim prediction circuitry also includes a second filter configured to generate a filtered pitch attitude based on a measured pitch attitude of the aircraft. The pitch trim prediction circuitry further includes output circuitry configured to generate a predicted pitch attitude trim value for a target vertical state based on a horizontal velocity of the aircraft, the filtered velocity, and the filtered pitch attitude. The predicted pitch attitude trim value is configured to cause a flight control effector to be adjusted.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: August 18, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Publication number: 20190332124
    Abstract: A control circuitry includes a propulsor trim prediction circuitry configured to generate a predicted propulsor collective blade pitch trim value for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference. The control circuitry further includes an output circuitry configured to output a propulsor collective blade pitch angle command based on the predicted propulsor collective blade pitch trim value. The propulsor collective blade pitch angle command is configured to cause an adjustment in a blade pitch angle of a propulsor of the aircraft. Additionally or alternatively, the control circuitry includes a pitch attitude trim prediction circuitry configured to generate a predicted pitch attitude trim value. The output circuitry is configured to output an aircraft pitch attitude trim command, configured to cause an adjustment in a pitch angle of the aircraft, based on the predicted pitch attitude trim value.
    Type: Application
    Filed: May 22, 2018
    Publication date: October 31, 2019
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Publication number: 20190332126
    Abstract: A control circuitry includes a first filter configured to filter a gravity compensated longitudinal acceleration of an aircraft to generate a filtered gravity compensated longitudinal acceleration. The propulsor trim control circuitry also includes a second filter configured to generate a filtered speed of the aircraft based on a speed of the aircraft. The propulsor trim control circuitry includes intermediary circuitry configured to generate a filtered longitudinal control effector error based on the filtered gravity compensated longitudinal acceleration and the speed. The propulsor trim control circuitry also includes a third filter configured to generate a filtered longitudinal thrust effector command value based on a longitudinal thrust effector command value.
    Type: Application
    Filed: May 22, 2018
    Publication date: October 31, 2019
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Publication number: 20190329879
    Abstract: A control circuitry includes a first filter configured to generate a filtered velocity based on a component of a vertical velocity of an aircraft. The pitch trim prediction circuitry also includes a second filter configured to generate a filtered pitch attitude based on a measured pitch attitude of the aircraft. The pitch trim prediction circuitry further includes output circuitry configured to generate a predicted pitch attitude trim value for a target vertical state based on a horizontal velocity of the aircraft, the filtered velocity, and the filtered pitch attitude. The predicted pitch attitude trim value is configured to cause a flight control effector to be adjusted.
    Type: Application
    Filed: May 22, 2018
    Publication date: October 31, 2019
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Publication number: 20190332125
    Abstract: A control circuitry includes a propulsor trim prediction circuitry and an output circuitry. The propulsor trim prediction circuitry is configured to generate a predicted proprotor nacelle trim value based on an aircraft velocity and a pitch attitude deviation from a reference. The output circuitry is configured to output a proprotor nacelle command based on the predicted proprotor nacelle trim value. The proprotor nacelle command is configured to cause an adjustment in a nacelle angle of a proprotor of an aircraft.
    Type: Application
    Filed: May 22, 2018
    Publication date: October 31, 2019
    Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
  • Patent number: 9156546
    Abstract: The system contains the active inceptor having mobility in a first direction. A feedback mechanism is in communication with the active inceptor. The mechanism provides a variable level of force to the active inceptor in the first direction. A programmable device communicates with the feedback mechanism. The programmable device controls the level of force provided to the active inceptor from the feedback mechanism. The programmable device is capable of recognizing and distinguishing between regimes wherein the operator is physically engaging the inceptor (“hands-on” state) and when the operator is “hands-off” the inceptor. The programmable device limits the maximum rate of displacement of an active inceptor to a specified safe and effective value regardless of changes in forces applied by the variable force feel feedback mechanism.
    Type: Grant
    Filed: March 11, 2008
    Date of Patent: October 13, 2015
    Assignee: THE BOEING COMPANY
    Inventors: Joseph G. Irwin, III, Pieter G. Einthoven, David G. Miller, Mark S. Spano
  • Publication number: 20090234518
    Abstract: The system contains the active inceptor having mobility in a first direction. A feedback mechanism is in communication with the active inceptor. The mechanism provides a variable level of force to the active inceptor in the first direction. A programmable device communicates with the feedback mechanism. The programmable device controls the level of force provided to the active inceptor from the feedback mechanism. The programmable device is capable of recognizing and distinguishing between regimes wherein the operator is physically engaging the inceptor (“hands-on” state) and when the operator is “hands-off” the inceptor. The programmable device limits the maximum rate of displacement of an active inceptor to a specified safe and effective value regardless of changes in forces applied by the variable force feel feedback mechanism.
    Type: Application
    Filed: March 11, 2008
    Publication date: September 17, 2009
    Inventors: Joseph G. Irwin, III, Pieter G. Einthoven, David G. Miller, Mark S. Spano