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公开(公告)号：US20130168492A1
公开(公告)日：2013-07-04
申请号：US13669212
申请日：2012-11-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph Biser , Clifton B. Day , Frank B. Stamps , Daniel Spivey
CPC classification number: B64C27/605 , F16C7/06 , F16C2326/43 , Y10T29/4973
Abstract: According to one embodiment, a pitch link includes a first link, a second link coupled to a first end of the first link, a third link coupled to a second end of the first link opposite the first end, and a first bearing housing having a first bearing and a second bearing housing having a second bearing. The first bearing housing is removably coupled to the second link. The second link separates the first bearing housing from the first link. The second bearing housing is removably coupled to the third link. The third link separates the second bearing housing from the first link.
Abstract translation: 根据一个实施例，节距连杆包括第一连杆，联接到第一连杆的第一端的第二连杆，联接到与第一端相对的第一连杆的第二端的第三连杆，以及具有 第一轴承和具有第二轴承的第二轴承壳体。 第一轴承壳体可拆卸地联接到第二连杆。 第二连杆将第一轴承箱与第一连杆分开。 第二轴承壳体可拆卸地联接到第三连杆。 第三连杆将第二轴承箱与第一连杆分开。
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公开(公告)号：US11014659B2
公开(公告)日：2021-05-25
申请号：US16042706
申请日：2018-07-23
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Troy Schank , Frank B. Stamps
IPC: B64C27/41 , B64C27/30 , B64C27/50 , B64C27/52 , B64C11/28 , B64C27/605 , B64C29/00 , B64C27/32 , B64C27/615
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：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：US20200023958A1
公开(公告)日：2020-01-23
申请号：US16399015
申请日：2019-04-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Aaron A. Acee , Albert G. Brand , Frank B. Stamps
Abstract: A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force.
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公开(公告)号：US20200023951A1
公开(公告)日：2020-01-23
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 , B64C11/50 , G10K11/178
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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Patent Agency Ranking
公开(公告)号：US10450058B2
公开(公告)日：2019-10-22
申请号：US15684385
申请日：2017-08-23
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：US10407157B2
公开(公告)日：2019-09-10
申请号：US13828495
申请日：2013-03-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Frank B. Stamps , Richard Rauber
Abstract: An apparatus comprising a spinner fairing assembly comprising a spinner configured to be fixed relative to a gimbaled yoke coupled to a mast system, and a spinner base configured to be fixed relative to the mast system. A spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.
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公开(公告)号：US10358207B2
公开(公告)日：2019-07-23
申请号：US15693397
申请日：2017-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps
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：US20190135423A1
公开(公告)日：2019-05-09
申请号：US15808801
申请日：2017-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Frank B. Stamps , Daniel B. Robertson , Matthew E. Louis
Abstract: In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.
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公开(公告)号：US20190127059A1
公开(公告)日：2019-05-02
申请号：US15796910
申请日：2017-10-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Levi C. Hefner , Frank B. Stamps
Abstract: There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.
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