Patents by Inventor Alan Carl Ewing
Alan Carl Ewing 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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Patent number: 11518504Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.Type: GrantFiled: May 25, 2021Date of Patent: December 6, 2022Assignee: Textron Innovations Inc.Inventors: Brent Chadwick Ross, Alan Carl Ewing, Steven Ray Ivans
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Patent number: 11267579Abstract: A hybrid propulsion engine for a rotorcraft includes a core turboshaft engine having a gas path and an output shaft that provides torque to a main rotor. A fan module is disposed relative to the core turboshaft engine and is coupled to the output shaft. The fan module has a bypass air path that is independent of the gas path. A thrust nozzle is configured to mix exhaust gases from the core turboshaft engine with bypass air from the fan module and to discharge the mixture to provide propulsive thrust. In a turboshaft configuration, the fan module is closed to prevent the flow of bypass air therethrough such that the thrust nozzle does not provide propulsive thrust. In a turboshaft and turbofan configuration, the fan module is open allowing the flow of bypass air therethrough such that the thrust nozzle provides propulsive thrust, thereby supplying propulsion compounding for the rotorcraft.Type: GrantFiled: March 26, 2019Date of Patent: March 8, 2022Assignee: Textron Innovations Inc.Inventors: Brent Chadwick Ross, Steven Ray Ivans, Alan Carl Ewing
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Publication number: 20210276703Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.Type: ApplicationFiled: May 25, 2021Publication date: September 9, 2021Applicant: Textron Innovations Inc.Inventors: Brent Chadwick Ross, Alan Carl Ewing, Steven Ray Ivans
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Patent number: 11052999Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.Type: GrantFiled: March 26, 2019Date of Patent: July 6, 2021Assignee: Textron Innovations Inc.Inventors: Brent Chadwick Ross, Alan Carl Ewing, Steven Ray Ivans
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Patent number: 10800526Abstract: An adapter is disclosed for use with an aircraft including wingtip stations defining mounting surfaces. The adapter is configured and dimensioned for connection to the wingtip stations on either wing of the aircraft to facilitate the connection of a weapons rack to the aircraft. The adapter includes a backing plate, and a body connected to the backing plate that is configured and dimensioned to support the weapons rack. The backing plate is configured and dimensioned in correspondence with the mounting surfaces defined by the wingtip stations. The body includes a base extending outwardly from the backing plate along a first axis, and a support member extending outwardly from the base along a second axis. In one particular embodiment of the adapter, the first and second axes define an angle of 45° therebetween.Type: GrantFiled: May 10, 2017Date of Patent: October 13, 2020Assignee: Textron Innovations Inc.Inventors: Alan Carl Ewing, Antonio Cardenas Munguia
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Publication number: 20200307779Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.Type: ApplicationFiled: March 26, 2019Publication date: October 1, 2020Applicant: Bell Textron Inc.Inventors: Brent Chadwick Ross, Alan Carl Ewing, Steven Ray Ivans
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Publication number: 20200309066Abstract: A hybrid propulsion engine for a rotorcraft includes a core turboshaft engine having a gas path and an output shaft that provides torque to a main rotor. A fan module is disposed relative to the core turboshaft engine and is coupled to the output shaft. The fan module has a bypass air path that is independent of the gas path. A thrust nozzle is configured to mix exhaust gases from the core turboshaft engine with bypass air from the fan module and to discharge the mixture to provide propulsive thrust. In a turboshaft configuration, the fan module is closed to prevent the flow of bypass air therethrough such that the thrust nozzle does not provide propulsive thrust. In a turboshaft and turbofan configuration, the fan module is open allowing the flow of bypass air therethrough such that the thrust nozzle provides propulsive thrust, thereby supplying propulsion compounding for the rotorcraft.Type: ApplicationFiled: March 26, 2019Publication date: October 1, 2020Applicant: Bell Textron Inc.Inventors: Brent Chadwick Ross, Steven Ray Ivans, Alan Carl Ewing
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Patent number: 10696391Abstract: A quad tiltrotor aircraft has a longitudinally extending fuselage with forward and aft stations. A forward wing having first and second outboard ends extends laterally from the forward station. An aft wing having first and second outboard ends extends laterally from the aft station. First and second forward rotors are respectively coupled proximate the first and second outboard ends of the forward wing and are tiltable relative to the forward wing between vertical lift and forward thrust orientations. First and second aft rotors are respectively coupled proximate the first and second outboard ends of the aft wing and are tiltable relative to the aft wing between vertical lift and forward thrust orientations. The forward rotors are higher disk-loading rotors than the aft rotors. The aft rotors are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft.Type: GrantFiled: November 16, 2017Date of Patent: June 30, 2020Assignee: Textron Innovations Inc.Inventors: Alan Carl Ewing, Eric Ricardo Gonzalez, Mark Loring Isaac, Frank Bradley Stamps
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Patent number: 10569870Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.Type: GrantFiled: November 18, 2016Date of Patent: February 25, 2020Assignee: Textron Innovations Inc.Inventors: Jouyoung Jason Choi, Gary Miller, Richard Erler Rauber, Thomas Clement Parham, Jr., Alan Carl Ewing, Frank Bradley Stamps
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Publication number: 20190144109Abstract: A quad tiltrotor aircraft has a longitudinally extending fuselage with forward and aft stations. A forward wing having first and second outboard ends extends laterally from the forward station. An aft wing having first and second outboard ends extends laterally from the aft station. First and second forward rotors are respectively coupled proximate the first and second outboard ends of the forward wing and are tiltable relative to the forward wing between vertical lift and forward thrust orientations. First and second aft rotors are respectively coupled proximate the first and second outboard ends of the aft wing and are tiltable relative to the aft wing between vertical lift and forward thrust orientations. The forward rotors are higher disk-loading rotors than the aft rotors. The aft rotors are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft.Type: ApplicationFiled: November 16, 2017Publication date: May 16, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Alan Carl Ewing, Eric Ricardo Gonzalez, Mark Loring Isaac, Frank Bradley Stamps
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Patent number: 10183743Abstract: 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: GrantFiled: July 11, 2017Date of Patent: January 22, 2019Assignee: Textron Innovations Inc.Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
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Publication number: 20180327094Abstract: An adapter is disclosed for use with an aircraft including wingtip stations defining mounting surfaces. The adapter is configured and dimensioned for connection to the wingtip stations on either wing of the aircraft to facilitate the connection of a weapons rack to the aircraft. The adapter includes a backing plate, and a body connected to the backing plate that is configured and dimensioned to support the weapons rack. The backing plate is configured and dimensioned in correspondence with the mounting surfaces defined by the wingtip stations. The body includes a base extending outwardly from the backing plate along a first axis, and a support member extending outwardly from the base along a second axis. In one particular embodiment of the adapter, the first and second axes define an angle of 45° therebetween.Type: ApplicationFiled: May 10, 2017Publication date: November 15, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Alan Carl Ewing, Antonio Cardenas Munguia
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Publication number: 20180141654Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.Type: ApplicationFiled: November 18, 2016Publication date: May 24, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Jouyoung Jason Choi, Gary Miller, Richard Erler Rauber, Thomas Clement Parham, JR., Alan Carl Ewing, Frank Bradley Stamps
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Publication number: 20180093762Abstract: 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: ApplicationFiled: July 11, 2017Publication date: April 5, 2018Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
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Patent number: 9701404Abstract: 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: GrantFiled: July 1, 2014Date of Patent: July 11, 2017Assignee: Textron Innovations Inc.Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
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Publication number: 20140316615Abstract: 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: ApplicationFiled: July 1, 2014Publication date: October 23, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
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Patent number: 8763950Abstract: 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: GrantFiled: September 3, 2013Date of Patent: July 1, 2014Assignee: Texron Innovations Inc.Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
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Publication number: 20140005862Abstract: 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: ApplicationFiled: September 3, 2013Publication date: January 2, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
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Patent number: 8523102Abstract: 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: GrantFiled: October 5, 2009Date of Patent: September 3, 2013Assignee: Textron Innovations Inc.Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
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Publication number: 20110180656Abstract: 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: ApplicationFiled: October 5, 2009Publication date: July 28, 2011Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing