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公开(公告)号：US20190061915A1
公开(公告)日：2019-02-28
申请号：US15693397
申请日：2017-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps
CPC classification number: B64C11/32 , B64C11/06 , B64C11/30 , B64C27/605 , B64C29/0033 , B64C2027/7216 , B64C2027/7255
Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
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公开(公告)号：US20190002085A1
公开(公告)日：2019-01-03
申请号：US15636448
申请日：2017-06-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Thomas Clement Parham, JR. , Gary Miller , Frank Bradley Stamps
IPC: B64C11/06 , B64C29/00 , B64C11/32 , F16F15/121
CPC classification number: B64C11/06 , B64C11/32 , B64C27/35 , B64C27/51 , B64C27/635 , B64C29/0033 , F16C23/043 , F16C27/02 , F16C2326/43 , F16F15/1208 , F16F15/121 , F16F15/124
Abstract: A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.
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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：US20190077502A1
公开(公告)日：2019-03-14
申请号：US15699677
申请日：2017-09-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Jason C. Owens , Frank B. Stamps , Andrew Paul Haldeman , Robert P. Wardlaw , John R. McCullough , Gary Miller , Andrew Ryan Maresh , Drew A. Sutton
Abstract: In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.
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公开(公告)号：US20190061929A9
公开(公告)日：2019-02-28
申请号：US15398919
申请日：2017-01-05
Applicant: Bell Helicopter Textron, Inc.
Inventor： Gary Miller , Frank B. Stamps
Abstract: An aircraft rotor assembly has a central yoke and a plurality of rotor blades coupled to the yoke for rotation with the yoke about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the yoke, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Lead and lag motion of each blade is opposed by a biasing force that biases 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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Patent Agency Ranking
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：US09499262B2
公开(公告)日：2016-11-22
申请号：US13958192
申请日：2013-08-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Frank B. Stamps , Joel McIntyre , Gary Miller
CPC classification number: B64C27/33 , B64C27/48 , B64C29/0033
Abstract: A composite flexure that secures a rotor blade to a gimbaled yoke in a tiltrotor rotor system. The composite flexure includes a composite flexure member, a first end, and a second end. The first end of the composite flexure couples the composite flexure to the gimbaled yoke, and the second end of the composite flexure couples the composite flexure to the rotor blade. The composite flexure is twisted when the composite flexure is not subject to torsional loads in order to accommodate various forces imparted on the rotor system.
Abstract translation: 复合弯曲，其将转子叶片固定在倾斜旋转器转子系统中的万向轭。 复合挠曲件包括复合挠曲构件，第一端和第二端。 复合挠曲件的第一端将复合挠曲件联接到万向架轭架上，并且复合挠曲件的第二端将复合挠曲件联接到转子叶片。 当复合挠曲件不受扭转载荷的影响时，复合挠曲是扭转的，以适应转子系统上施加的各种力。
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公开(公告)号：US20190375496A1
公开(公告)日：2019-12-12
申请号：US16547003
申请日：2019-08-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps
IPC: B64C27/33 , B64C27/605 , B64C29/00
Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
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公开(公告)号：US20190263502A1
公开(公告)日：2019-08-29
申请号：US16408057
申请日：2019-05-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps
IPC: B64C11/32 , B64C11/06 , B64C29/00 , B64C11/30 , B64C27/605
Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
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公开(公告)号：US20180186447A1
公开(公告)日：2018-07-05
申请号：US15398919
申请日：2017-01-05
Applicant: Bell Helicopter Textron, Inc.
Inventor： Gary Miller , Frank B. Stamps
Abstract: An aircraft rotor assembly has a central yoke and a plurality of rotor blades coupled to the yoke for rotation with the yoke about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the yoke, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Lead and lag motion of each blade is opposed by a biasing force that biases 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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