Patents by Inventor James I. Kern
James I. Kern 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: 7884565Abstract: A human-machine interface assembly includes a user interface and a passive force feedback mechanism. The user interface is configured, upon receipt of an input force that exceeds a null breakout force, to move from a null position to a first control position and, upon receipt of an input force that exceeds a soft stop force, to move beyond the first control position. The passive force feedback mechanism is coupled to the user interface and is configured to supply the null breakout force to the user interface when the user interface is in the null position, and supply the soft stop force to the user interface when the user interface is in the first control position. The soft stop force exceeds the null breakout force and is not supplied to the user interface unless the user interface is in the first control position.Type: GrantFiled: January 10, 2008Date of Patent: February 8, 2011Assignee: Honeywell International Inc.Inventors: James I Kern, James Casey Hanlon, Justin A. Tanner
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Patent number: 7866230Abstract: An apparatus is provided for biasing a shaft toward, and releasably securing it in, a predetermined position. The apparatus comprises a magnetic assembly coupled to the shaft for releasably securing the shaft in a predetermined position, a first member coupled to and extending from the shaft for rotating the shaft from the predetermined position, and a spring assembly coupled to the shaft for securing the shaft in the predetermined position.Type: GrantFiled: January 18, 2008Date of Patent: January 11, 2011Assignee: Honeywell International Inc.Inventors: Justin A. Tanner, Todd Langston, David Tornquist, Casey Hanlon, James I. Kern
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Patent number: 7812596Abstract: A position sensing system includes a plurality of two-axis anisotropic magneto-resistive (AMR) sensors to determine the position of a user interface. A magnetic member is coupled to the user interface, which is movable to a position along a random path. The plurality of two-axis AMR sensors is arranged in a two-dimensional sensor array that is spaced apart from the magnetic member. A signal processor circuit is operable to sense the electrical resistance values of each two-axis AMR sensor, to determine the position of the user interface from the resistance values, and to supply position feedback data representative of the determined position.Type: GrantFiled: August 16, 2007Date of Patent: October 12, 2010Assignee: Honeywell International Inc.Inventors: Calvin C. Potter, Casey Hanlon, Paul T. Wingett, James I. Kern
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Patent number: 7786684Abstract: Flight control systems and methods for rotorcraft are provided. The flight control system includes a user input device and a motor in operable communication with the user input device. The motor includes a plurality of winding sets and an armature coupled to the plurality of winding sets. The armature includes multiple magnets. The winding sets and the armature are configured such that when one or more of the plurality of winding sets are selectively energized, the armature moves relative to the one or more of the plurality of winding sets.Type: GrantFiled: October 22, 2007Date of Patent: August 31, 2010Assignee: Honeywell International Inc.Inventors: Casey Hanlon, James I. Kern
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Patent number: 7701161Abstract: An active user interface assembly includes a user interface, and one or more feedback motors coupled to the user interface. The one or more feedback motors, when energized, supply a feedback force to the user interface that opposes user interface movement. One of the feedback motors is disposed such that its center of gravity is located at a position relative to the user interface to mass balance the user interface when it is in the null position. The configurations allow for the center of gravity of a feedback motor to be positioned in a manner that alleviates the need for counterbalance weights.Type: GrantFiled: February 20, 2007Date of Patent: April 20, 2010Assignees: Honeywell International Inc., Wittenstein Aerospace & Simulation Ltd.Inventors: Casey Hanlon, James I. Kern, Douglas C. Smith, David Cowling
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Publication number: 20090178502Abstract: A human-machine interface assembly includes a user interface and a passive force feedback mechanism. The user interface is configured, upon receipt of an input force that exceeds a null breakout force, to move from a null position to a first control position and, upon receipt of an input force that exceeds a soft stop force, to move beyond the first control position. The passive force feedback mechanism is coupled to the user interface and is configured to supply the null breakout force to the user interface when the user interface is in the null position, and supply the soft stop force to the user interface when the user interface is in the first control position. The soft stop force exceeds the null breakout force and is not supplied to the user interface unless the user interface is in the first control position.Type: ApplicationFiled: January 10, 2008Publication date: July 16, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: James I. Kern, James Casey Hanlon, Justin A. Tanner
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Publication number: 20090178503Abstract: A human-machine interface assembly includes a user interface, a first null breakout force mechanism, and a second null breakout force mechanism. The first null breakout force mechanism is coupled to the user interface and is configured to supply the null breakout force to the user interface at a first force magnitude when the user interface is in the null position. The second null break out force mechanism is adapted to receive an engagement signal and is operable, in response to the engagement signal, to engage the user interface and supply the null breakout force to the user interface at a second force magnitude, which is greater than the first force magnitude, when the user interface is in the null position.Type: ApplicationFiled: January 10, 2008Publication date: July 16, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: James Casey Hanlon, James I. Kern, Justin A. Tanner
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Publication number: 20090102413Abstract: Flight control systems and methods for rotorcraft are provided. The flight control system includes a user input device and a motor in operable communication with the user input device. The motor includes a plurality of winding sets and an armature coupled to the plurality of winding sets. The armature includes multiple magnets. The winding sets and the armature are configured such that when one or more of the plurality of winding sets are selectively energized, the armature moves relative to the one or more of the plurality of winding sets.Type: ApplicationFiled: October 22, 2007Publication date: April 23, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Casey Hanlon, James I. Kern
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Publication number: 20090045979Abstract: A position sensing system includes a plurality of two-axis anisotropic magneto-resistive (AMR) sensors to determine the position of a user interface. A magnetic member is coupled to the user interface, which is movable to a position along a random path. The plurality of two-axis AMR sensors is arranged in a two-dimensional sensor array that is spaced apart from the magnetic member. A signal processor circuit is operable to sense the electrical resistance values of each two-axis AMR sensor, to determine the position of the user interface from the resistance values, and to supply position feedback data representative of the determined position.Type: ApplicationFiled: August 16, 2007Publication date: February 19, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Calvin C. Potter, Casey Hanlon, Paul T. Wingett, James I. Kern
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Publication number: 20080079381Abstract: An active user interface assembly includes a user interface, and one or more feedback motors coupled to the user interface. The one or more feedback motors, when energized, supply a feedback force to the user interface that opposes user interface movement. One of the feedback motors is disposed such that its center of gravity is located at a position relative to the user interface to mass balance the user interface when it is in the null position. The configurations allow for the center of gravity of a feedback motor to be positioned in a manner that alleviates the need for counterbalance weights.Type: ApplicationFiled: February 20, 2007Publication date: April 3, 2008Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Casey Hanlon, James I. Kern, Douglas C. Smith
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Patent number: 7007897Abstract: A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.Type: GrantFiled: June 22, 2004Date of Patent: March 7, 2006Assignee: Honeywell International, Inc.Inventors: Paul T. Wingett, Louie T. Gaines, Paul S. Evans, James I. Kern
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Patent number: 6827311Abstract: A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.Type: GrantFiled: April 7, 2003Date of Patent: December 7, 2004Assignee: Honeywell International, Inc.Inventors: Paul T. Wingett, Louie T. Gaines, Paul S. Evans, James I. Kern
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Publication number: 20040195441Abstract: A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.Type: ApplicationFiled: April 7, 2003Publication date: October 7, 2004Applicant: Honeywell International Inc.Inventors: Paul T. Wingett, Louie T. Gaines, Paul S. Evans, James I. Kern