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公开(公告)号：US10814963B2
公开(公告)日：2020-10-27
申请号：US16054606
申请日：2018-08-03
Applicant: Bell Helicopter Textron Inc.
Inventor： David E. Heverly, II , Jeremy DeWaters , Frank B. Stamps
Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
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公开(公告)号：US10648529B2
公开(公告)日：2020-05-12
申请号：US15820129
申请日：2017-11-21
Applicant: Bell Helicopter Textron Inc.
Inventor： David E. Heverly, II
IPC: B06B1/18 , F16F15/023 , B64C29/00
Abstract: In one embodiment, a centrifugal force generating device comprises a first hydraulic rotor, a second hydraulic rotor, and one or more hydraulic control valves. The first hydraulic rotor comprises a first mass and is configured to rotationally drive the first mass around a first axis of rotation using a first flow of hydraulic fluid through the first hydraulic rotor. The second hydraulic rotor comprises a second mass and is configured to rotationally drive the second mass around a second axis of rotation using a second flow of hydraulic fluid through the second hydraulic rotor. The one or more hydraulic control valves are configured to control the first flow of hydraulic fluid through the first hydraulic rotor and the second flow of hydraulic fluid through the second hydraulic rotor.
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公开(公告)号：US10112709B2
公开(公告)日：2018-10-30
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 , B64C27/51
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：US10065730B2
公开(公告)日：2018-09-04
申请号：US14600180
申请日：2015-01-20
Applicant: Bell Helicopter Textron Inc.
Inventor： David E. Heverly, II , Jeremy DeWaters , Frank B. Stamps
Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
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公开(公告)号：US20180038439A1
公开(公告)日：2018-02-08
申请号：US15723510
申请日：2017-10-03
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Taeoh Lee , David E. Heverly, II , Matthew W. Hendricks , Maurice Griffin , Michael R. Smith
CPC classification number: F16F7/00 , B64C27/001 , B64C2027/002 , F16F13/24
Abstract: The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.
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Patent Agency Ranking
16.发明申请ROTORCRAFT VIBRATION SUPPRESSION SYSTEM IN A FOUR CORNER PYLON MOUNT CONFIGURATION 有权四角墩安装配置中的ROTORCRAFT振动抑制系统公开(公告)号：US20130270415A1
公开(公告)日：2013-10-17
申请号：US13736687
申请日：2013-01-08
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Taeoh Lee , David E. Heverly, II , Matthew W. Hendricks , Maurice Griffin , Michael R. Smith
IPC: F16F7/00
CPC classification number: F16F7/00 , B64C27/001 , B64C2027/002 , F16F13/24
Abstract: The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.
Abstract translation: 振动抑制系统包括位于四角塔架安装结构组件的每个角落中的隔振器。 四个隔振器的组合，两个位于变速器前方，两个位于变速器的后面，共同有效地隔离主转子垂直剪切，俯仰力矩以及滚动力矩引起的振动。 每个相对的隔振器对可以有效地反应瞬间振动，因为瞬间可以在每个隔振器处分解成两个对立的垂直振荡。 吊架结构在一对隔振器之间延伸，从而允许隔振器与振动体隔开，以提供增加的控制。
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公开(公告)号：US20180370621A1
公开(公告)日：2018-12-27
申请号：US16054606
申请日：2018-08-03
Applicant: Bell Helicopter Textron Inc.
Inventor： David E. Heverly, II , Jeremy DeWaters , Frank B. Stamps
CPC classification number: B64C27/001 , B64C29/0033 , B64C2027/003
Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
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公开(公告)号：US09777788B2
公开(公告)日：2017-10-03
申请号：US13736687
申请日：2013-01-08
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Taeoh Lee , David E. Heverly, II , Matthew W. Hendricks , Maurice Griffin , Michael R. Smith
CPC classification number: F16F7/00 , B64C27/001 , B64C2027/002 , F16F13/24
Abstract: The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.
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公开(公告)号：US20170088257A1
公开(公告)日：2017-03-30
申请号：US14871615
申请日：2015-09-30
Applicant: Bell Helicopter Textron Inc.
Inventor： David E. Heverly, II , Rupinder Singh , Taeoh Lee , Michael Smith
CPC classification number: B64C27/001 , B64C27/06 , B64C2027/004 , F01D21/003 , F01D25/28
Abstract: A vibration control system for a rotorcraft includes at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator configured for association with a fuselage, and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.
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公开(公告)号：US09551393B2
公开(公告)日：2017-01-24
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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