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公开(公告)号：US11267561B2
公开(公告)日：2022-03-08
申请号：US16664675
申请日：2019-10-25
Applicant: Bell Textron Inc.
Inventor： David Heverly , Frank Bradley Stamps , Jouyoung Jason Choi , Michael R. Smith , Thomas C. Parham
Abstract: A vibration attenuator for a rotor of an aircraft has a track housing adapted for rotation relative to the rotor and configured for rotation at a second angular velocity greater than a first angular velocity of the rotor. A track is located within the track housing and has a reaction surface, a pair of weights being configured for movement within the track and in contact with the reaction surface. A stop assembly has a pair of stops spaced 180 degrees apart, the stops separating the weights from each other, and each weight being allowed to travel within the track between the stops. A motor rotates the track housing relative to the rotor. The weights are free to travel relative to each other between a minimum-force configuration, in which the weights are positioned 180 degrees apart, and a maximum-force configuration, in which both weights are adjacent one of the stops.
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公开(公告)号：US20200290725A1
公开(公告)日：2020-09-17
申请号：US16732198
申请日：2019-12-31
Applicant: Bell Textron Inc.
Inventor： Chad Lewis Jarrett , Frank Bradley Stamps , Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis , William Anthony Amante , Robert Vaughn , Joseph Richard Carpenter, JR.
Abstract: An aircraft has a ducted thruster. The ducted thruster includes a duct having an inner wall, a stator hub disposed within the duct, a first stator extending along a first longitudinal axis between the inner wall and the stator hub, and a second stator. The second stator extends along a second longitudinal axis between the inner wall and the stator hub. The second longitudinal axis is either (1) substantially perpendicular to the first longitudinal axis or (2) substantially parallel to the first longitudinal axis and offset from the first longitudinal axis.
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公开(公告)号：US11952111B2
公开(公告)日：2024-04-09
申请号：US16862276
申请日：2020-04-29
Applicant: Bell Textron Inc.
Inventor： Frank Bradley Stamps , Thomas C. Parham, Jr.
IPC: B64C27/605 , B64C27/57 , B64C27/64 , B64C27/68 , B64C29/00
CPC classification number: B64C29/0033 , B64C27/57 , B64C27/605 , B64C27/64 , B64C27/68
Abstract: A system is provided for controlling the pitch of blades of a rotor, the system comprising an actuator for each blade, each actuator being configured for selective control of the pitch of an associated blade about a pitch axis. Sensors are configured for determining aerodynamic forces acting on the rotor, and a flight control system is configured to receive signals from the sensors and for operating the actuators in response to the signals to achieve a desired pitch-flap coupling value.
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公开(公告)号：US11691723B2
公开(公告)日：2023-07-04
申请号：US17307845
申请日：2021-05-04
Applicant: Bell Textron Inc.
Inventor： Thomas C. Parham, Jr. , Frank Bradley Stamps , Jouyoung Jason Choi , Albert Gerard Brand , Michael Scott Seifert , Richard E. Rauber , John E. Brunken, Jr.
CPC classification number: B64C29/0033 , B64C11/008 , B64C11/02 , B64C11/32
Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.
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Patent Agency Ranking
公开(公告)号：US20210163128A1
公开(公告)日：2021-06-03
申请号：US16862276
申请日：2020-04-29
Applicant: Bell Textron Inc.
Inventor： Frank Bradley Stamps , Thomas C. Parham, Jr.
Abstract: A system is provided for controlling the pitch of blades of a rotor, the system comprising an actuator for each blade, each actuator being configured for selective control of the pitch of an associated blade about a pitch axis. Sensors are configured for determining aerodynamic forces acting on the rotor, and a flight control system is configured to receive signals from the sensors and for operating the actuators in response to the signals to achieve a desired pitch-flap coupling value.
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公开(公告)号：US11577825B2
公开(公告)日：2023-02-14
申请号：US16862257
申请日：2020-04-29
Applicant: Bell Textron Inc.
Inventor： Frank Bradley Stamps , David Heverly
Abstract: A vibration attenuator for a rotor of an aircraft has a housing adapted for rotation with the rotor about an axis. A first ring is rotatably carried within the housing on a first bearing, a first weight being coupled to the first ring for rotation therewith relative to the housing about the axis. A second ring is rotatably carried by the first ring on a second bearing, a second weight being coupled to the second ring for rotation therewith relative to the housing and to the first ring. A first motor is configured for rotating the first ring relative to the housing, and a second motor is configured for rotating the second ring relative to the housing and to the first ring. The first and second motors are operated to rotate the weights within the housing and position the weights relative to each other for attenuating vibrations.
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公开(公告)号：US20220355924A1
公开(公告)日：2022-11-10
申请号：US17307845
申请日：2021-05-04
Applicant: Bell Textron Inc.
Inventor： Thomas C. Parham, JR. , Frank Bradley Stamps , Jouyoung Jason Choi , Albert Gerard Brand , Michael Scott Seifert , Richard E. Rauber , John E. Brunken, JR.
Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.
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公开(公告)号：US20200255132A1
公开(公告)日：2020-08-13
申请号：US16862257
申请日：2020-04-29
Applicant: Bell Textron Inc.
Inventor： Frank Bradley Stamps , David Heverly
Abstract: A vibration attenuator for a rotor of an aircraft has a housing adapted for rotation with the rotor about an axis. A first ring is rotatably carried within the housing on a first bearing, a first weight being coupled to the first ring for rotation therewith relative to the housing about the axis. A second ring is rotatably carried by the first ring on a second bearing, a second weight being coupled to the second ring for rotation therewith relative to the housing and to the first ring. A first motor is configured for rotating the first ring relative to the housing, and a second motor is configured for rotating the second ring relative to the housing and to the first ring. The first and second motors are operated to rotate the weights within the housing and position the weights relative to each other for attenuating vibrations.
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公开(公告)号：US20210403148A1
公开(公告)日：2021-12-30
申请号：US17154925
申请日：2021-01-21
Applicant: Bell Textron Inc.
Inventor： Frank Bradley Stamps , Michael Reaugh Smith , Bradley Joseph Passe
Abstract: A compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.
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