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公开(公告)号：US20150336664A1
公开(公告)日：2015-11-26
申请号：US14283515
申请日：2014-05-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Richard E. Rauber , Mithat Yuce , Thomas C. Parham, JR. , Thomas J. Newman , Mark A. Wiinikka
CPC classification number: B64C27/54 , B64C27/51 , B64C27/58 , B64C27/59 , B64C27/635 , F16C11/045 , F16C11/0614 , F16C11/0695 , F16C23/02 , F16C2326/43
Abstract: An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.
Abstract translation: 飞机包括转子叶片和转子轮毂系统。 转子毂系统包括具有杆端并与转子叶片可操作地相关联的前导滞后阻尼器; 具有第一臂和相对的第二臂的刀片适配器; 由刀片适配器承载并被构造成经由第一臂和第二臂固定就位的销; 以及致动器，其固定到所述销并且构造成调节所述牵引杆延伸杆端部相对于所述第一臂和所述第二臂的位置。
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Patent Agency Ranking
公开(公告)号：US20190263512A1
公开(公告)日：2019-08-29
申请号：US16284931
申请日：2019-02-25
Applicant: Bell Helicopter Textron Inc.
Inventor： David Heverly , Frank Bradley Stamps , Gary Miller , Richard E. Rauber , Thomas C. Parham, JR. , Michael R. Smith , Michael Scott Seifert , Jouyoung Jason Choi
Abstract: A vibration attenuator for a rotor is rotatable about a mast axis and has a frame configured for rotation about the mast axis relative to the rotor. A first mass is axially translatable in a first direction relative to the frame parallel to a first axis, and a first biasing force urges the first mass toward a first-mass rest position in which the first mass is symmetric about the mast axis. A second mass is axially translatable in a second direction relative to the frame parallel to a second axis, and a second biasing force urges the second mass toward a second-mass rest position in which the second mass is symmetric about the mast axis. A selected first or second mass moves radially outward from the rest position to oppose vibrations in the rotor.
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公开(公告)号：US20170334552A1
公开(公告)日：2017-11-23
申请号：US15418652
申请日：2017-01-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael S. Seifert , Brett C. Howard , Thomas C. Parham, JR. , Martin Alex Peryea
CPC classification number: B64C27/001 , B64C5/02 , B64C27/04 , B64C29/0033 , B64C2027/8281 , F16F7/01 , F16F7/015 , F16F2224/0275
Abstract: In one embodiment, an apparatus comprises a particle damper for damping a component when the particle damper is attached to the component. The particle damper comprises a plurality of pockets configured to hold a plurality of particles, and the particle damper also comprises an attachment fitting for coupling the particle damper to the component.
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公开(公告)号：US20170320567A1
公开(公告)日：2017-11-09
申请号：US15432910
申请日：2017-02-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps , Jouyoung Jason Choi , Thomas C. Parham, JR. , Alan Ewing , Richard E. Rauber
IPC: B64C27/635 , B64C27/605 , B64C27/72
CPC classification number: B64C27/635 , B64C27/33 , B64C27/605 , B64C27/72 , B64C29/0033 , B64C2027/7255
Abstract: An aircraft rotor assembly has a central hub and a plurality of rotor blades coupled to the hub for rotation with the hub about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is formed by a flexure coupling the associated blade to the hub. Each pivot is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the hub, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure produces a biasing force for biasing the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.
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公开(公告)号：US20170253327A1
公开(公告)日：2017-09-07
申请号：US15603119
申请日：2017-05-23
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Richard E. Rauber , Mithat Yuce , Thomas C. Parham, JR. , Thomas J. Newman , Mark A. Wiinikka
Abstract: An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.
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公开(公告)号：US20200156773A1
公开(公告)日：2020-05-21
申请号：US16197761
申请日：2018-11-21
Applicant: Bell Helicopter Textron 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 for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.
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