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公开(公告)号：US11084575B2
公开(公告)日：2021-08-10
申请号：US16084970
申请日：2017-03-14
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Bradley 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：US10759530B2
公开(公告)日：2020-09-01
申请号：US16172326
申请日：2018-10-26
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： David E. Heverly, II , Frank B. Stamps , Michael Smith
IPC: B64C27/635 , B64C27/51
Abstract: A rotor system includes a hub assembly, a first, second, and third rotor blade rotatably attached to the hub assembly, a first, second, and third damper pivotally attached to the hub assembly and pivotally attached to the first, second, and third rotor blade, respectively, and a control system operably associated with the first, second, and third damper. A method to control vibratory forces exerted on the hub assembly via the first and second rotor blade includes separately controlling a dynamic spring rate of each of the first and second dampers with the control system.
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公开(公告)号：US20190061931A1
公开(公告)日：2019-02-28
申请号：US16172326
申请日：2018-10-26
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： David E. Heverly, II , Frank B. Stamps , Michael Smith
IPC: B64C27/635 , B64C27/51
CPC classification number: B64C27/635 , B64C27/51
Abstract: A rotor system includes a hub assembly, a first, second, and third rotor blade rotatably attached to the hub assembly, a first, second, and third damper pivotally attached to the hub assembly and pivotally attached to the first, second, and third rotor blade, respectively, and a control system operably associated with the first, second, and third damper. A method to control vibratory forces exerted on the hub assembly via the first and second rotor blade includes separately controlling a dynamic spring rate of each of the first and second dampers with the control system.
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公开(公告)号：US20190061923A1
公开(公告)日：2019-02-28
申请号：US16100679
申请日：2018-08-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Smith , Cheng-Ho Tho , Anand Kumar Marimuthu
Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.
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公开(公告)号：US09725165B2
公开(公告)日：2017-08-08
申请号：US14506286
申请日：2014-10-03
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Smith , Cheng-Ho Tho , Anand Kumar Marimuthu
CPC classification number: B64C27/006 , B26D1/12 , B26D1/25 , B26D2001/006 , B26D2001/0066
Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.
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Patent Agency Ranking
公开(公告)号：US10562617B2
公开(公告)日：2020-02-18
申请号：US15350073
申请日：2016-11-13
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Brad 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：US10479488B2
公开(公告)日：2019-11-19
申请号：US16100679
申请日：2018-08-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Smith , Cheng-Ho Tho , Anand Kumar Marimuthu
Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.
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公开(公告)号：US20170259911A1
公开(公告)日：2017-09-14
申请号：US15350073
申请日：2016-11-13
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Brad Stamps , Thomas Parham, JR. , Amarjit Olenchery Kizhakkepat
IPC: B64C27/00
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：US20160083088A1
公开(公告)日：2016-03-24
申请号：US14494036
申请日：2014-09-23
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： David E. Heverly, II , Frank B. Stamps , Michael Smith
IPC: B64C27/635 , B64C27/64 , B64C27/51
CPC classification number: B64C27/635 , B64C27/51
Abstract: A rotor system includes a hub assembly, a first, second, and third rotor blade rotatably attached to the hub assembly, a first, second, and third damper pivotally attached to the hub assembly and pivotally attached to the first, second, and third rotor blade, respectively, and a control system operably associated with the first, second, and third damper. A method to control vibratory forces exerted on the hub assembly via the first and second rotor blade includes separately controlling a dynamic spring rate of each of the first and second dampers with the control system.
Abstract translation: 转子系统包括轮毂组件，可旋转地附接到轮毂组件的第一，第二和第三转子叶片，枢转地附接到轮毂组件并枢转地附接到第一，第二和第三转子的第一，第二和第三阻尼器 刀片，以及与第一，第二和第三阻尼器可操作地相关联的控制系统。 控制经由第一和第二转子叶片施加在轮毂组件上的振动力的方法包括用控制系统分别控制第一和第二阻尼器中的每一个的动态弹簧刚度。
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公开(公告)号：US20150308534A1
公开(公告)日：2015-10-29
申请号：US14259757
申请日：2014-04-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Smith , Frank Bradley Stamps , Taeoh Lee , David E. Heverly, II
CPC classification number: F16F7/1034 , B64C27/001 , B64C2027/002
Abstract: A rotorcraft vibration isolation system includes a plurality of liquid inertia vibration elimination (LIVE) units mounted on a first rotorcraft surface, an accumulator mounted on a second rotorcraft surface at a location that is remote from locations of the plurality of LIVE units, and a fluid passage to connect the accumulator to the plurality of LIVE units in parallel. The fluid passage has sufficient length to traverse between the location of the accumulator and each location of each LIVE unit. During rotorcraft operation, the second rotorcraft surface experiences lesser periodic vibration than the first rotorcraft surface.
Abstract translation: 旋翼航空器的隔振系统包括安装在第一旋翼飞机表面上的多个液体惯性振动消除（LIVE）单元，在远离多个LIVE单元的位置的位置处安装在第二旋翼航空器表面上的蓄能器，以及流体 通道将蓄能器并联连接到多个LIVE单元。 流体通道具有足够的长度以在蓄能器的位置和每个LIVE单元的每个位置之间穿过。 在旋翼航空器操作期间，第二旋翼飞机表面经历比第一旋翼飞机表面更小的周期性振动。
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