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公开(公告)号：US11585400B2
公开(公告)日：2023-02-21
申请号：US16782019
申请日：2020-02-04
Applicant: Textron Innovations Inc.
Abstract: 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.
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公开(公告)号：US11440648B2
公开(公告)日：2022-09-13
申请号：US16855706
申请日：2020-04-22
Applicant: Textron Innovations Inc.
Inventor： Peter Quinn Romano , Frank Bradley Stamps , Michael Scott Seifert
Abstract: 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.
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公开(公告)号：US11724800B2
公开(公告)日：2023-08-15
申请号：US17567874
申请日：2022-01-03
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , David Heverly , Michael R. Smith , Michael Scott Seifert , Thomas C Parham, Jr. , Gary Miller , Jouyoung Jason Choi , Richard E. Rauber
IPC: B64C27/00
CPC classification number: B64C27/001 , B64C2027/003 , B64C2027/005
Abstract: 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.
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公开(公告)号：US11565802B2
公开(公告)日：2023-01-31
申请号：US17154650
申请日：2021-01-21
Applicant: Textron Innovations Inc.
Abstract: 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.
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公开(公告)号：US11326661B2
公开(公告)日：2022-05-10
申请号：US16293040
申请日：2019-03-05
Applicant: TEXTRON INNOVATIONS INC.
Inventor： Michael Scott Seifert , Peter Quinn Romano , Thomas Parham
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20210331787A1
公开(公告)日：2021-10-28
申请号：US16855706
申请日：2020-04-22
Applicant: Textron Innovations Inc.
Inventor： Peter Quinn Romano , Frank Bradley Stamps , Michael Scott Seifert
Abstract: 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.
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公开(公告)号：US11767107B2
公开(公告)日：2023-09-26
申请号：US16504057
申请日：2019-07-05
Applicant: TEXTRON INNOVATIONS INC.
Inventor： Matthew Carl VanBuskirk , Michael Scott Seifert
CPC classification number: B64C29/0091 , B64C7/00 , B64C27/001 , B64C29/0033 , F16F7/108 , F16F7/1034 , F16F2222/08
Abstract: 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.
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公开(公告)号：US20220227486A1
公开(公告)日：2022-07-21
申请号：US17154650
申请日：2021-01-21
Applicant: Textron Innovations Inc.
Abstract: 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.
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公开(公告)号：US20220126989A1
公开(公告)日：2022-04-28
申请号：US17567874
申请日：2022-01-03
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , David Heverly , Michael R. Smith , Michael Scott Seifert , Thomas C. Parham, JR. , Gary Miller , Jouyoung Jason Choi , Richard E. Rauber
IPC: B64C27/00
Abstract: 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.
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公开(公告)号：US11203418B2
公开(公告)日：2021-12-21
申请号：US16717095
申请日：2019-12-17
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , Michael Reaugh Smith , Michael Scott Seifert
Abstract: 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.
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