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公开(公告)号：US11173521B2
公开(公告)日：2021-11-16
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：US20180290738A1
公开(公告)日：2018-10-11
申请号：US16006552
申请日：2018-06-12
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Richard E. Rauber , Frank B. Stamps
Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.
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公开(公告)号：US09365288B2
公开(公告)日：2016-06-14
申请号：US13678272
申请日：2012-11-15
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Frank B. Stamps , Richard E. Rauber
IPC: B64C27/78 , B64C27/605
CPC classification number: B64C27/605
Abstract: The present application includes a blade-pitch control system with an indexing swashplate. A swashplate assembly has a non-rotating portion and a rotating portion and an indexing portion of the mast. The swashplate assembly is translatably affixed to the indexing portion. A pitch link connects the rotating portion of the swashplate assembly to each blade. Translation of the swashplate assembly along the indexing portion causes a change in pitch of the blades and a corresponding indexing of the rotating portion of the swashplate assembly relative to the mast, the indexing causing a change in an angular orientation of each pitch link, thus providing for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.
Abstract translation: 本申请包括具有索引斜盘的叶片桨距控制系统。 斜盘组件具有非旋转部分和桅杆的旋转部分和分度部分。 斜盘组件可平移地固定到分度部分。 间距连杆将旋转斜盘组件的旋转部分连接到每个叶片。 斜盘组件沿着分度部分的平移导致叶片间距的变化以及斜盘组件相对于桅杆的旋转部分的相应分度，引导引起每个节距连杆的角取向的改变，从而提供 用于在轭的拍动运动和叶片的俯仰运动之间选择的桨距翼片耦合。
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Patent Agency Ranking
公开(公告)号：US20140322010A1
公开(公告)日：2014-10-30
申请号：US13872480
申请日：2013-04-29
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Richard E. Rauber , Frank B. Stamps
IPC: B64C27/41
CPC classification number: B64C27/41 , B64C27/32 , B64C29/0033
Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.
Abstract translation: 本申请提供了用于飞行器转子的等速度接头的驱动连杆，该连杆将连接到驱动轴的驱动轮毂连接到转子轭。 连杆包括连接到驱动轮毂的前导轴承，连接到轭的后轴承，轴承之间的中心部分和连接轴承的张力环。 张力环由复合材料形成并形成为连续带。 张力环将驱动力从前导轴承传递到后轴承，用于驱动轭与驱动轴一起旋转。
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公开(公告)号：US11214361B2
公开(公告)日：2022-01-04
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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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：US20140133980A1
公开(公告)日：2014-05-15
申请号：US13678272
申请日：2012-11-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank B. Stamps , Richard E. Rauber
IPC: B64C27/78
CPC classification number: B64C27/605
Abstract: The present application includes a blade-pitch control system with an indexing swashplate. A swashplate assembly has a non-rotating portion and a rotating portion and an indexing portion of the mast. The swashplate assembly is translatably affixed to the indexing portion. A pitch link connects the rotating portion of the swashplate assembly to each blade. Translation of the swashplate assembly along the indexing portion causes a change in pitch of the blades and a corresponding indexing of the rotating portion of the swashplate assembly relative to the mast, the indexing causing a change in an angular orientation of each pitch link, thus providing for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.
Abstract translation: 本申请包括具有索引斜盘的叶片桨距控制系统。 斜盘组件具有非旋转部分和桅杆的旋转部分和分度部分。 斜盘组件可平移地固定到分度部分。 间距连杆将旋转斜盘组件的旋转部分连接到每个叶片。 斜盘组件沿着分度部分的平移导致叶片间距的变化以及斜盘组件相对于桅杆的旋转部分的相应分度，引导引起每个节距连杆的角度定向的改变，从而提供 用于在轭的拍动运动和叶片的俯仰运动之间选择的桨距翼片耦合。
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