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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：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：US10654558B2
公开(公告)日：2020-05-19
申请号：US15938979
申请日：2018-03-28
Applicant: Textron Innovations Inc.
Inventor： Jouyoung Jason Choi , Frank B. Stamps
Abstract: One example of a rotor assembly comprises: a rotor hub operable to rotate based on rotation of a mast; a first rotor blade pivotally attached to the rotor hub; a bracing member pivotally attached to the rotor hub at a first end and pivotally attached to the first rotor blade at a second end; and a linkage mechanism coupling the first rotor blade to a second rotor blade. The bracing member is operable to transfer a coning movement of the first rotor blade to a movement of the linkage mechanism and a corresponding coning movement of the second rotor blade.
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公开(公告)号：US10518867B2
公开(公告)日：2019-12-31
申请号：US15375356
申请日：2016-12-12
Applicant: Textron Innovations Inc.
Inventor： Thomas Clement Parham, Jr. , Jouyoung Jason Choi , Gary Miller , Frank Bradley Stamps , Richard Erler Rauber
IPC: B64C11/04 , B64C11/06 , B29C70/30 , B64C27/00 , B64C27/33 , B64C27/35 , B64C27/51 , B64C27/54 , B64C29/00 , B29C70/32 , B29K105/08 , B29K307/04 , B29L31/30
Abstract: A yoke for providing a centrifugal force retention load path between a proprotor blade and a hub of a soft-in-plane proprotor system operable for use on a tiltrotor aircraft. The yoke includes a continuous loop having a longitudinal axis and first and second longitudinal sections extending between inboard and outboard arcuate sections. A flapping bearing receiving region is disposed at least partially within the inboard arcuate section to an interior of the continuous loop. A centrifugal force bearing receiving region is disposed at least partially within the outboard arcuate section to the interior of the continuous loop. The continuous loop is formed from a composite material having a plurality of double bias material plies and a plurality of unidirectional material plies such that the number of unidirectional material plies is greater than the number of double bias material plies.
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公开(公告)号：US20240101250A1
公开(公告)日：2024-03-28
申请号：US18307343
申请日：2023-04-26
Applicant: TEXTRON INNOVATIONS INC.
Inventor： Carlos Alexander Fenny , Jouyoung Jason Choi
CPC classification number: B64C27/08 , B64C39/062 , B64D27/26 , G05D1/0202 , G05D1/0808 , B64D2027/262
Abstract: An aircraft comprises a fuselage, a plurality of support structures coupled to the fuselage, and a first propeller and a second propeller connected to a motor and symmetrically distributed along the plurality of support structures, the first propeller configured to create a first thrust having a first horizontal force vector and the second propeller configured to create a second thrust having a second horizontal force vector. A summation of the first and second horizontal force vectors is substantially zero when the first thrust is substantially equal to the second thrust, and a first rotational axis of the first propeller and a second rotational axis of the second propeller are substantially coplanar with a vertical axis disposed between the first and second propeller. A movement of the aircraft is controlled by selectively increasing or decreasing a thrust of either the first propeller or the second propeller.
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公开(公告)号：US11697491B2
公开(公告)日：2023-07-11
申请号：US17038893
申请日：2020-09-30
Applicant: Textron Innovations Inc.
Inventor： Carlos Fenny , Sung Kim , Kip Campbell , Jouyoung Jason Choi
CPC classification number: B64C15/14 , B64C29/0016 , F04D25/06
Abstract: An electric reaction control system that can selectively expel a “burst” or “puff” of air to alter the orientation of the aircraft during flight. An aircraft incorporating ducting, an air compressor, an electric motor, and a plurality of nozzles can facilitate in-flight trajectory modifications. When an air burst is needed to provide thrust for the purposes of reaction control, nozzles are selectively opened and closed to provide roll, pitch, and yaw of the aircraft. The ERCS can facilitate an electric aircraft that would be very agile and very light, utilizing electric power, as opposed to jet power.
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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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