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公开(公告)号：US11066157B2
公开(公告)日：2021-07-20
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：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：US20200055593A1
公开(公告)日：2020-02-20
申请号：US16042706
申请日：2018-07-23
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Troy Schank , Frank B. Stamps
IPC: B64C27/30 , B64C27/41 , B64C27/615 , B64C27/32 , B64C29/00 , B64C27/605 , B64C11/28 , B64C27/52 , B64C27/50
Abstract: A method of selectively preventing flapping of a rotor hub includes providing a flapping lock proximate to a rotor hub and shaft assembly and moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft.
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公开(公告)号：US10549849B1
公开(公告)日：2020-02-04
申请号：US15895589
申请日：2018-02-13
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Brian Modrzejewski , Ken Shundo , Frank B. Stamps , David Popelka , J. Scott Drennan , Michael E. Rinehart
IPC: B64C27/00 , F16F15/22 , B64C11/50 , G10K11/178 , B64C27/30
Abstract: An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.
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公开(公告)号：US10472057B2
公开(公告)日：2019-11-12
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
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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Patent Agency Ranking
公开(公告)号：US10450060B2
公开(公告)日：2019-10-22
申请号：US15229461
申请日：2016-08-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Clifton B. Day , Frank B. Stamps , Jason Hoyle
Abstract: A laminated elastomeric bearing has layers of elastomeric material and layers of metal. A tab is located on a periphery of one of the layers of metal and protrudes from the bearing. A thermoelectric device is coupled to the tab, and heat generated within the bearing during use is conducted to the tab and to the thermoelectric device, allowing for measurement of the heat.
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公开(公告)号：US20190300152A1
公开(公告)日：2019-10-03
申请号：US15938979
申请日：2018-03-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Frank B. Stamps
Abstract: One example of a rotor assembly comprises: a rotor hub operable to rotate based on rotation of a mast; a first rotor blade pivotally attached to the rotor hub; a bracing member pivotally attached to the rotor hub at a first end and pivotally attached to the first rotor blade at a second end; and a linkage mechanism coupling the first rotor blade to a second rotor blade. The bracing member is operable to transfer a coning movement of the first rotor blade to a movement of the linkage mechanism and a corresponding coning movement of the second rotor blade.
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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：US20180170534A1
公开(公告)日：2018-06-21
申请号：US15900226
申请日：2018-02-20
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Hunter Davis , Frank B. Stamps
Abstract: The bearing system is configured for treating and reacting dynamic loading within a rotor hub of rotorcraft. The bearing system includes an outer member having a plurality of alternating outer elastomeric layers and shim layers. The outer member has an inboard surface configured for bonding to an inboard bearing support, and the outer member has an outboard surface configured for bonding to an outboard bearing support. The bearing system has an inner member bonded to an interior surface of the outer member. The inner member can include a rigid inner core, as well as a plurality of elastomeric layers and shim layers configured to react torsional movements of the rotor blade.
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公开(公告)号：US09994311B2
公开(公告)日：2018-06-12
申请号：US13872480
申请日：2013-04-29
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Richard E. Rauber , Frank B. Stamps
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.
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