Patents by Inventor Stephen Kubik
Stephen Kubik 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).
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Publication number: 20240125872Abstract: The present disclosure provides a magnetoresistive (xMR) sensor that has enhanced immunity to the presence of a magnetic cross field by using a combination of differential biasing on the sensing layers of the sensing elements, sensing elements having different sensitivities, and different reference magnetization directions. The xMR sensor comprises two or more arrays of sensing elements, wherein each array comprises a plurality of sensing elements. The sensing elements within each array may be arranged in pairs, wherein the sensor elements within each pair have sensing layers that are magnetically biased in antiparallel directions. The sensing elements within each array are also provided with different respective sensitivities. The sensing elements having the lowest sensitivity are provided with a reference layer magnetised in a first direction, and the sensing elements in the remaining arrays are provided with a reference layer magnetised in a direction that is antiparallel to the first direction.Type: ApplicationFiled: September 26, 2023Publication date: April 18, 2024Inventors: Fernando Franco, Jan Kubik, Jochen Schmitt, Stephen O'Brien
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Publication number: 20230373618Abstract: Systems and methods for transitioning between rotor positions based on detected parameters of an aircraft. One embodiment provides an aircraft comprising a rotor assembly and a controller. The controller is configured to monitor an operating characteristic of the aircraft. The controller is configured to select, in response to a rotor neutral state of the aircraft being enabled, one of a plurality of rotor neutral positions based on the operating characteristic, the plurality of rotor neutral positions including a first rotor neutral position configured for vertical takeoff of the aircraft and a second rotor neutral position configured for start-up and shutdown of the aircraft. The controller is configured to set the selected one of the plurality of rotor neutral positions as the rotor neutral position for the aircraft.Type: ApplicationFiled: May 18, 2022Publication date: November 23, 2023Inventors: Adam A. Leone, Stephen Kubik, Kevin Wrona, Benjamin J. Williamson
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Patent number: 10864986Abstract: A rotary aerial vehicle (AV) includes an engine configured to rotate at least one rotor at a variable rotor speed, a full authority electronic microcontroller (FAEM) in electrical communication with the engine. The FAEM is configured to output at least one electronic engine control signal that controls operation of the engine. An electronic rotor speed microcontroller (ERSM) is in electrical communication with the FAEM, and the ERSM is configured to dynamically determine at least one mission objective of the rotary AV, and outputs an electronic rotor speed control signal that commands the FAEM to adjust the rotor speed of the at least one rotor.Type: GrantFiled: March 18, 2016Date of Patent: December 15, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Stephen Kubik, Derek Geiger
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Patent number: 10705527Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.Type: GrantFiled: March 27, 2018Date of Patent: July 7, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Kenneth S. Wittmer, Stephen Kubik
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Patent number: 10351225Abstract: A method for position hold override control of an aircraft includes determining, by a processor, that a position hold mode is enabled to hold the aircraft at a substantially fixed position with respect to a target. The processor receives a control input indicative of a commanded change in acceleration of the aircraft as an override of the position hold mode. The processor determines an acceleration command based on the commanded change in acceleration. The acceleration command is adjusted as an adjusted acceleration command responsive to a non-linear scheduled translational rate command based on feedback of a commanded velocity of the aircraft. An update to the commanded velocity of the aircraft is generated based on the adjusted acceleration command.Type: GrantFiled: March 4, 2016Date of Patent: July 16, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Steven E. Spoldi, Alex Faynberg, Stephen Kubik, Donald T. Ream, John Rucci, Stephen C. McCulley, Christiaan Corry
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Publication number: 20180257770Abstract: A rotary aerial vehicle (AV) includes an engine configured to rotate at least one rotor at a variable rotor speed, a full authority electronic microcontroller (FAEM) in electrical communication with the engine. The FAEM is configured to output at least one electronic engine control signal that controls operation of the engine. An electronic rotor speed microcontroller (ERSM) is in electrical communication with the FAEM, and the ERSM is configured to dynamically determine at least one mission objective of the rotary AV, and outputs an electronic rotor speed control signal that commands the FAEM to adjust the rotor speed of the at least one rotor.Type: ApplicationFiled: March 18, 2016Publication date: September 13, 2018Inventors: Stephen Kubik, Derek Geiger
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Patent number: 10073455Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.Type: GrantFiled: March 11, 2016Date of Patent: September 11, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Kenneth S. Wittmer, Stephen Kubik
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Publication number: 20180217602Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.Type: ApplicationFiled: March 27, 2018Publication date: August 2, 2018Inventors: Kenneth S. Wittmer, Stephen Kubik
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Publication number: 20180141642Abstract: A method for position hold override control of an aircraft includes determining, by a processor, that a position hold mode is enabled to hold the aircraft at a substantially fixed position with respect to a target. The processor receives a control input indicative of a commanded change in acceleration of the aircraft as an override of the position hold mode. The processor determines an acceleration command based on the commanded change in acceleration. The acceleration command is adjusted as an adjusted acceleration command responsive to a non-linear scheduled translational rate command based on feedback of a commanded velocity of the aircraft. An update to the commanded velocity of the aircraft is generated based on the adjusted acceleration command.Type: ApplicationFiled: March 4, 2016Publication date: May 24, 2018Inventors: Steven E. Spoldi, Alex Faynberg, Stephen Kubik, Donald T. Ream, John Rucci, Stephen C. McCulley, Christiaan Corry
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Patent number: 9964960Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, wings extending outwardly from the fuselage to define a wing plane and a prop-rotor operably disposed to generate thrust, a flight computer and controllable surfaces disposed on at least one of the fuselage, the wings and the prop-rotor. The controllable surfaces are controllable by the flight computer to position the wing plane in accordance with a predominant local wind direction.Type: GrantFiled: June 17, 2016Date of Patent: May 8, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Cody Fegely, Stephen Kubik
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Patent number: 9908615Abstract: A rotor blown wing (RBW) aircraft including an airframe, at least one rotor blown wing (RBW) having at least control selectively controllable surface, at least one rotor configured to generate and direct an airflow over the at least one RBW, and a control system operatively connected to the at least two selectively controllable control surfaces. The control system selectively controls the at least one selectively controllable control surface to change the airflow over the at least one RBW to facilitate a vertical landing.Type: GrantFiled: August 11, 2016Date of Patent: March 6, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Mark R. Alber, Jeffery Parkhurst, Cody Fegely, Stephen Kubik
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Patent number: 9727059Abstract: One aspect is a flight control system for independent speed and attitude control of a rotary wing aircraft that includes a main rotor system and a translational thrust system. The flight control system includes a flight control computer configured to interface with the main rotor system and the translational thrust system. The flight control computer includes processing circuitry configured to execute control logic. A pitch attitude reference generator provides a pitch attitude reference to a main rotor controller to command the main rotor system based on pilot input. A longitudinal reference generator produces a longitudinal reference as a longitudinal position or longitudinal velocity based on pilot input. An attitude-to-propulsor crossfeed converts the pitch attitude reference into a propulsor trim adjustment. A propeller pitch controller combines the longitudinal reference and the propulsor trim adjustment into a propeller command, and provides the propeller command to the translational thrust system.Type: GrantFiled: June 17, 2015Date of Patent: August 8, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Aaron L. Greenfield, John Knag, Stephen Kubik
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Publication number: 20170158312Abstract: A rotor blown wing (RBW) aircraft including an airframe, at least one rotor blown wing (RBW) having at least control selectively controllable surface, at least one rotor configured to generate and direct an airflow over the at least one RBW, and a control system operatively connected to the at least two selectively controllable control surfaces. The control system selectively controls the at least one selectively controllable control surface to change the airflow over the at least one RBW to facilitate a vertical landing.Type: ApplicationFiled: August 11, 2016Publication date: June 8, 2017Inventors: Mark R. Alber, Jeffery Parkhurst, Cody Fegely, Stephen Kubik
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Publication number: 20170097644Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, wings extending outwardly from the fuselage to define a wing plane and a prop-rotor operably disposed to generate thrust, a flight computer and controllable surfaces disposed on at least one of the fuselage, the wings and the prop-rotor. The controllable surfaces are controllable by the flight computer to position the wing plane in accordance with a predominant local wind direction.Type: ApplicationFiled: June 17, 2016Publication date: April 6, 2017Inventors: Cody Fegely, Stephen Kubik
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Publication number: 20170021924Abstract: A tail sitter aircraft is capable of forward flight and hover operations. The tail sitter aircraft includes a wing and first and second prop-nacelles supportively disposed on the wing. Each of the first and second prop-nacelles includes an articulable rotor, which is rotatable about variable rotational axes and which includes blades that are collectively and cyclically controllable in both forward flight and hover regimes.Type: ApplicationFiled: May 18, 2016Publication date: January 26, 2017Inventors: Stephen Kubik, Joseph T. Driscoll, Frank P. D'Anna, Mark R. Alber, Timothy Fred Lauder, Cody Fegely
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Publication number: 20160195874Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.Type: ApplicationFiled: March 11, 2016Publication date: July 7, 2016Inventors: Kenneth S. Wittmer, Stephen Kubik
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Patent number: 9360869Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.Type: GrantFiled: December 3, 2013Date of Patent: June 7, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Kenneth S. Wittmer, Stephen Kubik
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Publication number: 20160147227Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.Type: ApplicationFiled: December 3, 2013Publication date: May 26, 2016Applicant: Sikorsky Aircraft CorporationInventors: Kenneth S. Wittmer, Stephen Kubik
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Patent number: 9308985Abstract: A system and method for controlling a deceleration profile of an aircraft, includes a processor and memory that receives a signal indicative of a deceleration command; receives signals indicative of a sensed velocity and a commanded heading rate; determines a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate; determines an estimated deceleration command as a function of the commanded velocity; and determines an actual deceleration command in response to the determining of the estimated deceleration command.Type: GrantFiled: April 11, 2014Date of Patent: April 12, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Stephen Kubik, Alex Faynberg, Stephen C. Mcculley, John P. Rucci, Christiaan P. Corry, Edward Pavelka
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Publication number: 20150367937Abstract: One aspect is a flight control system for independent speed and attitude control of a rotary wing aircraft that includes a main rotor system and a translational thrust system. The flight control system includes a flight control computer configured to interface with the main rotor system and the translational thrust system. The flight control computer includes processing circuitry configured to execute control logic. A pitch attitude reference generator provides a pitch attitude reference to a main rotor controller to command the main rotor system based on pilot input. A longitudinal reference generator produces a longitudinal reference as a longitudinal position or longitudinal velocity based on pilot input. An attitude-to-propulsor crossfeed converts the pitch attitude reference into a propulsor trim adjustment. A propeller pitch controller combines the longitudinal reference and the propulsor trim adjustment into a propeller command, and provides the propeller command to the translational thrust system.Type: ApplicationFiled: June 17, 2015Publication date: December 24, 2015Inventors: Aaron L. Greenfield, John Knag, Stephen Kubik