Patents by Inventor Michael Scott Seifert
Michael Scott Seifert 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: 11767107Abstract: A vibratory motion reduction system for a pylon assembly includes an inner member having an opening extending therein that receives a first end of the pylon assembly, an outer member moveably attached to the inner member, a tuning mass attached to the inner member and the outer member such that a vibratory motion of the pylon assembly accelerates the tuning mass, a spring member that couples to a second end of the pylon assembly, and the spring member and the tuning mass reduce the vibratory motion of the pylon assembly.Type: GrantFiled: July 5, 2019Date of Patent: September 26, 2023Assignee: TEXTRON INNOVATIONS INC.Inventors: Matthew Carl VanBuskirk, Michael Scott Seifert
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Patent number: 11724800Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.Type: GrantFiled: January 3, 2022Date of Patent: August 15, 2023Assignee: Textron Innovations Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C Parham, Jr., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Patent number: 11691723Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.Type: GrantFiled: May 4, 2021Date of Patent: July 4, 2023Assignee: Textron Innovations Inc.Inventors: Thomas C. Parham, Jr., Frank Bradley Stamps, Jouyoung Jason Choi, Albert Gerard Brand, Michael Scott Seifert, Richard E. Rauber, John E. Brunken, Jr.
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Patent number: 11585400Abstract: An aircraft, has an airframe, a transmission, and a liquid inertia vibration elimination (LIVE) system disposed between the airframe and the transmission via spherical bearings of two legs and via a central spherical bearing.Type: GrantFiled: February 4, 2020Date of Patent: February 21, 2023Assignee: Textron Innovations Inc.Inventors: Michael Scott Seifert, Frederick Sullivan Gay, Dalton T. Hampton, Frank Bradley Stamps
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Patent number: 11565802Abstract: A rotor system for a rotorcraft includes a rotor hub having a plurality of blade grips coupled thereto. Each blade grip has a rotor blade coupled thereto. A fairing is disposed at least partially around the rotor hub. Each of a plurality of lead-lag dampers is coupled to at least a respective one of the blade grips. Each lead-lag damper has a damper heat exchanger and a fluid pump operably associated therewith. A fairing heat exchanger is in fluid communication with the damper heat exchangers and the fluid pumps. Each lead-lag damper is configured to drive the respective fluid pump responsive to damping operations to pump a cooling fluid from the respective damper heat exchanger to the fairing heat exchanger.Type: GrantFiled: January 21, 2021Date of Patent: January 31, 2023Assignee: Textron Innovations Inc.Inventors: Aaron Alexander Acee, Andrew Thomas Carter, Michael Scott Seifert, Shahryar Fotovati
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Publication number: 20220355924Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.Type: ApplicationFiled: May 4, 2021Publication date: November 10, 2022Applicant: Bell Textron Inc.Inventors: Thomas C. Parham, JR., Frank Bradley Stamps, Jouyoung Jason Choi, Albert Gerard Brand, Michael Scott Seifert, Richard E. Rauber, John E. Brunken, JR.
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Patent number: 11440648Abstract: A liquid inertia vibration eliminator unit for an aircraft having first and second components includes an outer housing coupled to the first component of the aircraft, the outer housing forming an outer housing cavity. The liquid inertia vibration eliminator unit includes a spherical bearing disposed in the outer housing cavity and forming a spherical bearing cavity. A piston is disposed in the spherical bearing cavity and coupled to the second component of the aircraft. Top and bottom fluid chambers are disposed in the spherical bearing cavity on opposite sides of the piston. A tuning passage provides fluid communication between the top and bottom fluid chambers. A tuning fluid moves between the top and bottom fluid chambers via the tuning passage to isolate vibration between the first and second components of the aircraft.Type: GrantFiled: April 22, 2020Date of Patent: September 13, 2022Assignee: Textron Innovations Inc.Inventors: Peter Quinn Romano, Frank Bradley Stamps, Michael Scott Seifert
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Publication number: 20220227486Abstract: A rotor system for a rotorcraft includes a rotor hub having a plurality of blade grips coupled thereto. Each blade grip has a rotor blade coupled thereto. A fairing is disposed at least partially around the rotor hub. Each of a plurality of lead-lag dampers is coupled to at least a respective one of the blade grips. Each lead-lag damper has a damper heat exchanger and a fluid pump operably associated therewith. A fairing heat exchanger is in fluid communication with the damper heat exchangers and the fluid pumps. Each lead-lag damper is configured to drive the respective fluid pump responsive to damping operations to pump a cooling fluid from the respective damper heat exchanger to the fairing heat exchanger.Type: ApplicationFiled: January 21, 2021Publication date: July 21, 2022Applicant: Textron Innovations Inc.Inventors: Aaron Alexander Acee, Andrew Thomas Carter, Michael Scott Seifert, Shahryar Fotovati
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Patent number: 11326661Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.Type: GrantFiled: March 5, 2019Date of Patent: May 10, 2022Assignee: TEXTRON INNOVATIONS INC.Inventors: Michael Scott Seifert, Peter Quinn Romano, Thomas Parham
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Publication number: 20220126989Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.Type: ApplicationFiled: January 3, 2022Publication date: April 28, 2022Applicant: Textron Innovations Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C. Parham, JR., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Patent number: 11214361Abstract: A vibration attenuator for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.Type: GrantFiled: November 21, 2018Date of Patent: January 4, 2022Assignee: Textron Innovations Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C. Parham, Jr., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Patent number: 11203418Abstract: A mount system for tiltably supporting a pylon assembly of a rotorcraft. First, second, third and fourth pylon links are each coupled between the pylon assembly and the airframe of the rotorcraft. The first pylon link has a first axis, the second pylon link has a second axis, the third pylon link has a third axis and the fourth pylon link has a fourth axis. Each of the axes intersects at a focal point located proximate a coaxial rotor system having counter-rotating upper and lower rotor assemblies such that the focal point provides a virtual pivot point about which the pylon assembly tilts to generate a control moment about a center of gravity of the rotorcraft that counteracts lateral and fore/aft moments generated by the upper and lower rotor assemblies during rotorcraft maneuvers.Type: GrantFiled: December 17, 2019Date of Patent: December 21, 2021Assignee: Textron Innovations Inc.Inventors: Frank Bradley Stamps, Michael Reaugh Smith, Michael Scott Seifert
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Patent number: 11173521Abstract: A vibration attenuator for a rotor is rotatable about a mast axis and has a frame configured for rotation about the mast axis relative to the rotor. A first mass is axially translatable in a first direction relative to the frame parallel to a first axis, and a first biasing force urges the first mass toward a first-mass rest position in which the first mass is symmetric about the mast axis. A second mass is axially translatable in a second direction relative to the frame parallel to a second axis, and a second biasing force urges the second mass toward a second-mass rest position in which the second mass is symmetric about the mast axis. A selected first or second mass moves radially outward from the rest position to oppose vibrations in the rotor.Type: GrantFiled: February 25, 2019Date of Patent: November 16, 2021Assignee: Textron Innovations Inc.Inventors: David Heverly, Frank Bradley Stamps, Gary Miller, Richard E. Rauber, Thomas C. Parham, Jr., Michael R. Smith, Michael Scott Seifert, Jouyoung Jason Choi
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Publication number: 20210331787Abstract: A liquid inertia vibration eliminator unit for an aircraft having first and second components includes an outer housing coupled to the first component of the aircraft, the outer housing forming an outer housing cavity. The liquid inertia vibration eliminator unit includes a spherical bearing disposed in the outer housing cavity and forming a spherical bearing cavity. A piston is disposed in the spherical bearing cavity and coupled to the second component of the aircraft. Top and bottom fluid chambers are disposed in the spherical bearing cavity on opposite sides of the piston. A tuning passage provides fluid communication between the top and bottom fluid chambers. A tuning fluid moves between the top and bottom fluid chambers via the tuning passage to isolate vibration between the first and second components of the aircraft.Type: ApplicationFiled: April 22, 2020Publication date: October 28, 2021Applicant: Textron Innovations Inc.Inventors: Peter Quinn Romano, Frank Bradley Stamps, Michael Scott Seifert
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Publication number: 20210001980Abstract: A vibratory motion reduction system for a pylon assembly includes an inner member having an opening extending therein that receives a first end of the pylon assembly, an outer member moveably attached to the inner member, a tuning mass attached to the inner member and the outer member such that a vibratory motion of the pylon assembly accelerates the tuning mass, a spring member that couples to a second end of the pylon assembly, and the spring member and the tuning mass reduce the vibratory motion of the pylon assembly.Type: ApplicationFiled: July 5, 2019Publication date: January 7, 2021Inventors: Matthew Carl VanBuskirk, Michael Scott Seifert
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Publication number: 20200398976Abstract: A mount system for tiltably supporting a pylon assembly of a rotorcraft. First, second, third and fourth pylon links are each coupled between the pylon assembly and the airframe of the rotorcraft. The first pylon link has a first axis, the second pylon link has a second axis, the third pylon link has a third axis and the fourth pylon link has a fourth axis. Each of the axes intersects at a focal point located proximate a coaxial rotor system having counter-rotating upper and lower rotor assemblies such that the focal point provides a virtual pivot point about which the pylon assembly tilts to generate a control moment about a center of gravity of the rotorcraft that counteracts lateral and fore/aft moments generated by the upper and lower rotor assemblies during rotorcraft maneuvers.Type: ApplicationFiled: December 17, 2019Publication date: December 24, 2020Applicant: Bell Textron Inc.Inventors: Frank Bradley Stamps, Michael Reaugh Smith, Michael Scott Seifert
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Patent number: 10843788Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly. The damping sublayer reduces the deflection of the wing, thereby stabilizing the wing during forward flight.Type: GrantFiled: June 29, 2017Date of Patent: November 24, 2020Assignee: Textron Innovations Inc.Inventors: Thomas Clement Parham, Jr., Jeffrey Bosworth, Gary Miller, Frank Bradley Stamps, Jouyoung Jason Choi, Paul K. Oldroyd, Richard Erler Rauber, Michael Scott Seifert
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Publication number: 20200173512Abstract: An aircraft, has an airframe, a transmission, and a liquid inertia vibration elimination (LIVE) system disposed between the airframe and the transmission via spherical bearings of two legs and via a central spherical bearing.Type: ApplicationFiled: February 4, 2020Publication date: June 4, 2020Applicant: Textron Innovations Inc.Inventors: Michael Scott Seifert, Frederick Sullivan Gay, Dalton T. Hampton, Frank Bradley Stamps
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Publication number: 20200156773Abstract: A vibration attenuator for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.Type: ApplicationFiled: November 21, 2018Publication date: May 21, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C. Parham, JR., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Patent number: 10550907Abstract: A liquid inertia vibration elimination (LIVE) system having an upper end cap, a lower end cap, a spindle located between the upper end cap and the lower end cap, and an external tube connected between the upper end cap and the lower end cap.Type: GrantFiled: August 18, 2016Date of Patent: February 4, 2020Assignee: Textron Innovations Inc.Inventors: Michael Scott Seifert, Frederick Sullivan Gay, Dalton T. Hampton, Frank Brad Stamps