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: 11016506Abstract: 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: GrantFiled: May 22, 2018Date of Patent: May 25, 2021Assignee: THE BOEING COMPANYInventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Patent number: 10935985Abstract: 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: GrantFiled: May 22, 2018Date of Patent: March 2, 2021Assignee: THE BOEING COMPANYInventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Patent number: 10877487Abstract: 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: GrantFiled: May 22, 2018Date of Patent: December 29, 2020Assignee: THE BOEING COMPANYInventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Patent number: 10747235Abstract: 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: GrantFiled: May 22, 2018Date of Patent: August 18, 2020Assignee: THE BOEING COMPANYInventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Publication number: 20190332124Abstract: 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: ApplicationFiled: May 22, 2018Publication date: October 31, 2019Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Publication number: 20190332126Abstract: 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: ApplicationFiled: May 22, 2018Publication date: October 31, 2019Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Publication number: 20190329879Abstract: 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: ApplicationFiled: May 22, 2018Publication date: October 31, 2019Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Publication number: 20190332125Abstract: 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: ApplicationFiled: May 22, 2018Publication date: October 31, 2019Inventors: Joseph G. Irwin, III, David G. Miller, Nathaniel T. Morgan
-
Patent number: 9156546Abstract: 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: GrantFiled: March 11, 2008Date of Patent: October 13, 2015Assignee: THE BOEING COMPANYInventors: Joseph G. Irwin, III, Pieter G. Einthoven, David G. Miller, Mark S. Spano
-
Publication number: 20090234518Abstract: 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: ApplicationFiled: March 11, 2008Publication date: September 17, 2009Inventors: Joseph G. Irwin, III, Pieter G. Einthoven, David G. Miller, Mark S. Spano