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公开(公告)号：US11148790B2
公开(公告)日：2021-10-19
申请号：US16794075
申请日：2020-02-18
Applicant: Textron Innovations Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Stamps , Thomas Parham, Jr. , Amarjit Olenchery Kizhakkepat
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
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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：US11577826B2
公开(公告)日：2023-02-14
申请号：US17689511
申请日：2022-03-08
Applicant: Textron Innovations Inc.
Inventor： David Heverly , Frank Bradley Stamps , Jouyoung Jason Choi , Michael R. Smith , Thomas C. Parham
Abstract: A vibration attenuator for a rotor of an aircraft has a first ring with an eccentric weight, a coaxial second ring with an eccentric weight, and a central ring coaxial with the first and second rings and located therebetween. A first post extends from the first ring toward the central ring and is received in a first arcuate groove formed on the central ring, whereas a second post extends from the second ring toward the central ring and is received in a second groove formed on the central ring. A motor is configured for driving the central ring in rotation about the axis relative to the motor. The grooves are equal in length, and a center of the first groove is located on an opposite side from a center of the second groove. Rotation of the central ring by the motor causes rotation of the first and second rings.
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公开(公告)号：US11685521B2
公开(公告)日：2023-06-27
申请号：US17397956
申请日：2021-08-09
Applicant: Textron Innovations Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Bradley Stamps , Thomas C. Parham, Jr. , Amarjit Olenchery Kizhakkepat
CPC classification number: B64C27/001 , F16F7/116 , B64C2027/003 , F16F15/14
Abstract: A vibration attenuator has a first spinner configured for rotation about a first axis and a first mass coupled to the first spinner for rotation therewith, the first mass being movable radially relative to the first axis between an inner position and an outer position. An actuator is coupled to the first mass for selectively controlling a radial location of the first mass relative to the axis, and a first motor is configured for driving the first spinner in rotation about the first axis.
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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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Patent Agency Ranking
公开(公告)号：US10526076B2
公开(公告)日：2020-01-07
申请号：US15277756
申请日：2016-09-27
Applicant: Textron Innovations Inc.
Inventor： David Heverly , David A. Popelka , Frank B. Stamps
Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other.
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公开(公告)号：US20220194567A1
公开(公告)日：2022-06-23
申请号：US17689511
申请日：2022-03-08
Applicant: Textron Innovations Inc.
Inventor： David Heverly , Frank Bradley Stamps , Jouyoung Jason Choi , Michael R. Smith , Thomas C. Parham
Abstract: A vibration attenuator for a rotor of an aircraft has a first ring with an eccentric weight, a coaxial second ring with an eccentric weight, and a central ring coaxial with the first and second rings and located therebetween. A first post extends from the first ring toward the central ring and is received in a first arcuate groove formed on the central ring, whereas a second post extends from the second ring toward the central ring and is received in a second groove formed on the central ring. A motor is configured for driving the central ring in rotation about the axis relative to the motor. The grooves are equal in length, and a center of the first groove is located on an opposite side from a center of the second groove. Rotation of the central ring by the motor causes rotation of the first and second rings.
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公开(公告)号：US20210362842A1
公开(公告)日：2021-11-25
申请号：US17397956
申请日：2021-08-09
Applicant: Textron Innovations Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Bradley Stamps , Thomas C. Parham, JR. , Amarjit Olenchery Kizhakkepat
Abstract: A vibration attenuation system as shown and described.
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公开(公告)号：US20200239133A1
公开(公告)日：2020-07-30
申请号：US16794075
申请日：2020-02-18
Applicant: Textron Innovations Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Stamps , Thomas Parham, JR. , Amarjit Olenchery Kizhakkepat
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
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公开(公告)号：US20170297685A1
公开(公告)日：2017-10-19
申请号：US15277756
申请日：2016-09-27
Applicant: Textron Innovations Inc.
Inventor： David Heverly , David A. Popelka , Frank B. Stamps
CPC classification number: B64C27/001 , B64C11/008 , B64C29/0033 , B64C2027/003 , B64C2027/004 , B64C2027/005
Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other.
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