Patents by Inventor Thomas C. Parham, JR.
Thomas C. Parham, JR. has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11952111Abstract: 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.Type: GrantFiled: April 29, 2020Date of Patent: April 9, 2024Assignee: Textron Innovations Inc.Inventors: Frank Bradley Stamps, Thomas C. Parham, Jr.
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Patent number: 11724800Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.Type: GrantFiled: January 3, 2022Date of Patent: August 15, 2023Assignee: Textron Innovations Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C Parham, Jr., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Patent number: 11691723Abstract: 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.Type: GrantFiled: May 4, 2021Date of Patent: July 4, 2023Assignee: Textron Innovations Inc.Inventors: Thomas C. Parham, Jr., Frank Bradley Stamps, Jouyoung Jason Choi, Albert Gerard Brand, Michael Scott Seifert, Richard E. Rauber, John E. Brunken, Jr.
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Patent number: 11685521Abstract: A vibration attenuator has a first spinner configured for rotation about a first axis and a first mass coupled to the first spinner for rotation therewith, the first mass being movable radially relative to the first axis between an inner position and an outer position. An actuator is coupled to the first mass for selectively controlling a radial location of the first mass relative to the axis, and a first motor is configured for driving the first spinner in rotation about the first axis.Type: GrantFiled: August 9, 2021Date of Patent: June 27, 2023Assignee: Textron Innovations Inc.Inventors: Jouyoung Jason Choi, David Heverly, Michael Seifert, Michael Smith, Frank Bradley Stamps, Thomas C. Parham, Jr., Amarjit Olenchery Kizhakkepat
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Publication number: 20220355924Abstract: 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.Type: ApplicationFiled: May 4, 2021Publication date: November 10, 2022Applicant: Bell Textron Inc.Inventors: Thomas C. Parham, JR., Frank Bradley Stamps, Jouyoung Jason Choi, Albert Gerard Brand, Michael Scott Seifert, Richard E. Rauber, John E. Brunken, JR.
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Publication number: 20220126989Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.Type: ApplicationFiled: January 3, 2022Publication date: April 28, 2022Applicant: Textron Innovations Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C. Parham, JR., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Patent number: 11214361Abstract: 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.Type: GrantFiled: November 21, 2018Date of Patent: January 4, 2022Assignee: Textron Innovations Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C. Parham, Jr., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Publication number: 20210362842Abstract: A vibration attenuation system as shown and described.Type: ApplicationFiled: August 9, 2021Publication date: November 25, 2021Applicant: Textron Innovations Inc.Inventors: Jouyoung Jason Choi, David Heverly, Michael Seifert, Michael Smith, Frank Bradley Stamps, Thomas C. Parham, JR., Amarjit Olenchery Kizhakkepat
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Patent number: 11173521Abstract: 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.Type: GrantFiled: February 25, 2019Date of Patent: November 16, 2021Assignee: Textron Innovations Inc.Inventors: David Heverly, Frank Bradley Stamps, Gary Miller, Richard E. Rauber, Thomas C. Parham, Jr., Michael R. Smith, Michael Scott Seifert, Jouyoung Jason Choi
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Publication number: 20210163128Abstract: 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.Type: ApplicationFiled: April 29, 2020Publication date: June 3, 2021Applicant: Bell Textron Inc.Inventors: Frank Bradley Stamps, Thomas C. Parham, Jr.
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Patent number: 10875636Abstract: A rotor system for a rotorcraft has a hub rotatable about an axis and a plurality of blades coupled to the hub for rotation therewith about the axis. Each blade is capable of rotation about a pitch axis relative to the hub, and a ring couples adjacent blades to each other.Type: GrantFiled: November 20, 2018Date of Patent: December 29, 2020Assignee: Textron Innovations Inc.Inventors: Eric Albert Sinusas, Thomas C. Parham, Jr., Albert Gerard Brand
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Publication number: 20200156773Abstract: 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.Type: ApplicationFiled: November 21, 2018Publication date: May 21, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Frank Bradley Stamps, David Heverly, Michael R. Smith, Michael Scott Seifert, Thomas C. Parham, JR., Gary Miller, Jouyoung Jason Choi, Richard E. Rauber
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Publication number: 20200156775Abstract: A rotor system for a rotorcraft has a hub rotatable about an axis and a plurality of blades coupled to the hub for rotation therewith about the axis. Each blade is capable of rotation about a pitch axis relative to the hub, and a ring couples adjacent blades to each other.Type: ApplicationFiled: November 20, 2018Publication date: May 21, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Eric Albert Sinusas, Thomas C. Parham, Jr., Albert Gerard Brand
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Patent number: 10647418Abstract: In one embodiment, an apparatus comprises a particle damper for damping a component when the particle damper is attached to the component. The particle damper comprises a plurality of pockets configured to hold a plurality of particles, and the particle damper also comprises an attachment fitting for coupling the particle damper to the component.Type: GrantFiled: January 27, 2017Date of Patent: May 12, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Michael S. Seifert, Brett C. Howard, Thomas C. Parham, Jr., Martin Alex Peryea
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Patent number: 10532810Abstract: 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.Type: GrantFiled: May 23, 2017Date of Patent: January 14, 2020Inventors: Richard E. Rauber, Mithat Yuce, Thomas C. Parham, Jr., Thomas J. Newman, Mark A. Wiinikka
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Patent number: 10472057Abstract: 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.Type: GrantFiled: February 14, 2017Date of Patent: November 12, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Gary Miller, Frank B. Stamps, Jouyoung Jason Choi, Thomas C. Parham, Jr., Alan Ewing, Richard E. Rauber
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Publication number: 20190263512Abstract: 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.Type: ApplicationFiled: February 25, 2019Publication date: August 29, 2019Applicant: Bell Helicopter Textron Inc.Inventors: David Heverly, Frank Bradley Stamps, Gary Miller, Richard E. Rauber, Thomas C. Parham, JR., Michael R. Smith, Michael Scott Seifert, Jouyoung Jason Choi
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Publication number: 20170334552Abstract: In one embodiment, an apparatus comprises a particle damper for damping a component when the particle damper is attached to the component. The particle damper comprises a plurality of pockets configured to hold a plurality of particles, and the particle damper also comprises an attachment fitting for coupling the particle damper to the component.Type: ApplicationFiled: January 27, 2017Publication date: November 23, 2017Inventors: Michael S. Seifert, Brett C. Howard, Thomas C. Parham, JR., Martin Alex Peryea
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Publication number: 20170320567Abstract: 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.Type: ApplicationFiled: February 14, 2017Publication date: November 9, 2017Applicant: Bell Helicopter Textron Inc.Inventors: Gary Miller, Frank B. Stamps, Jouyoung Jason Choi, Thomas C. Parham, JR., Alan Ewing, Richard E. Rauber
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Publication number: 20170253327Abstract: 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.Type: ApplicationFiled: May 23, 2017Publication date: September 7, 2017Inventors: Richard E. Rauber, Mithat Yuce, Thomas C. Parham, JR., Thomas J. Newman, Mark A. Wiinikka