Patents by Inventor Richard E. Rauber
Richard E. Rauber 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: 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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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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Patent number: 11396371Abstract: A rotor hub assembly that includes a yoke configured to attach blades thereto, a universal joint configured to attach to, and transmit forces between, a mast and the yoke, and an elastomeric member configured to attenuate vibrations transmitted from the universal joint to the mast.Type: GrantFiled: September 8, 2020Date of Patent: July 26, 2022Assignee: Textron Innovations Inc.Inventors: Richard E. Rauber, Frank Bradley Stamps
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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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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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Patent number: 11066157Abstract: 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.Type: GrantFiled: June 12, 2018Date of Patent: July 20, 2021Assignee: Bell Textron Inc.Inventors: Richard E. Rauber, Frank B. Stamps
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Publication number: 20200407054Abstract: A rotor hub assembly that includes a yoke configured to attach blades thereto, a universal joint configured to attach to, and transmit forces between, a mast and the yoke, and an elastomeric member configured to attenuate vibrations transmitted from the universal joint to the mast.Type: ApplicationFiled: September 8, 2020Publication date: December 31, 2020Applicant: Textron Innovations Inc.Inventors: Richard E. Rauber, Frank Bradley Stamps
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Patent number: 10766612Abstract: A rotor hub assembly that includes a yoke configured to attach blades thereto, a universal joint configured to attach to, and transmit forces between, a mast and the yoke, and an elastomeric member configured to attenuate vibrations transmitted from the universal joint to the mast.Type: GrantFiled: July 24, 2017Date of Patent: September 8, 2020Assignee: Textron Innovations Inc.Inventors: Richard E. Rauber, Frank Bradley Stamps
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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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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: 20190023386Abstract: A rotor hub assembly that includes a yoke configured to attach blades thereto, a universal joint configured to attach to, and transmit forces between, a mast and the yoke, and an elastomeric member configured to attenuate vibrations transmitted from the universal joint to the mast.Type: ApplicationFiled: July 24, 2017Publication date: January 24, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Richard E. Rauber, Frank Bradley Stamps
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Publication number: 20180290738Abstract: 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.Type: ApplicationFiled: June 12, 2018Publication date: October 11, 2018Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Richard E. Rauber, Frank B. Stamps
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Patent number: 9994311Abstract: 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.Type: GrantFiled: April 29, 2013Date of Patent: June 12, 2018Assignee: Bell Helicopter Textron Inc.Inventors: Richard E. Rauber, Frank B. Stamps
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Patent number: 9878782Abstract: A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.Type: GrantFiled: February 17, 2015Date of Patent: January 30, 2018Assignee: Textron Innovations Inc.Inventors: Frank B. Stamps, Patrick R. Tisdale, Tom Donovan, Richard E. Rauber
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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