Patents by Inventor Andrew Haldeman
Andrew Haldeman 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: 11932125Abstract: A system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprises: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.Type: GrantFiled: November 29, 2021Date of Patent: March 19, 2024Assignee: TEXTRON INNOVATIONS INC.Inventors: Andrew Haldeman, Eric A. Sinusas, Frank Bradley Stamps
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Publication number: 20220080842Abstract: A system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprises: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.Type: ApplicationFiled: November 29, 2021Publication date: March 17, 2022Inventors: Andrew Haldeman, Eric A. Sinusas, Frank Bradley Stamps
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Patent number: 11186185Abstract: The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.Type: GrantFiled: May 31, 2017Date of Patent: November 30, 2021Assignee: TEXTRON INNOVATIONS INC.Inventors: Andrew Haldeman, Eric Sinusas, Frank Bradley Stamps
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Patent number: 10654567Abstract: A rotor blade assembly includes a rotor blade comprising an inboard end and an outboard end. A composite yoke fitting made from a composite material is attached to the rotor blade. The composite yoke fitting includes an outboard portion inserted into the inboard end of the rotor blade, an inboard portion, and a flexure region about which the rotor blade is configured to flex. The inboard portion and the flexure region are outside the rotor blade.Type: GrantFiled: March 26, 2015Date of Patent: May 19, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Haldeman, Frank Bradley Stamps, Drew Sutton
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Patent number: 10569867Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.Type: GrantFiled: August 10, 2018Date of Patent: February 25, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Maresh, Frank Bradley Stamps, Patrick Ryan Tisdale, Robert Patrick Wardlaw, Andrew Haldeman, Drew Alan Sutton
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Patent number: 10384771Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.Type: GrantFiled: May 19, 2017Date of Patent: August 20, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Haldeman, Frank Bradley Stamps, Drew Alan Sutton, James Donn Hethcock
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Patent number: 10336445Abstract: An apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein a center portion of each longitudinal side portion comprises a build-up of material that is configured to accommodate a yoke hub clamp. Included is an apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. Also included is a method of coupling aircraft blades comprising providing a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions.Type: GrantFiled: March 12, 2013Date of Patent: July 2, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Maresh, Frank Bradley Stamps, Andrew Haldeman
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Publication number: 20180346109Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.Type: ApplicationFiled: August 10, 2018Publication date: December 6, 2018Inventors: Andrew Maresh, Frank Bradley Stamps, Patrick Ryan Tisdale, Robert Patrick Wardlaw, Andrew Haldeman, Drew Alan Sutton
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Publication number: 20180346135Abstract: The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.Type: ApplicationFiled: May 31, 2017Publication date: December 6, 2018Inventors: Andrew Haldeman, Eric Sinusas, Frank Bradley Stamps
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Patent number: 10086934Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.Type: GrantFiled: November 28, 2016Date of Patent: October 2, 2018Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Maresh, Frank Bradley Stamps, Patrick Ryan Tisdale, Robert Patrick Wardlaw, Andrew Haldeman, Drew Alan Sutton
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Publication number: 20170259913Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.Type: ApplicationFiled: May 19, 2017Publication date: September 14, 2017Inventors: Andrew Haldeman, Frank Bradley Stamps, Drew Alan Sutton, James Donn Hethcock
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Patent number: 9657582Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.Type: GrantFiled: March 13, 2013Date of Patent: May 23, 2017Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Haldeman, Frank Bradley Stamps, Drew Sutton, James Donn Hethcock
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Publication number: 20170073067Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.Type: ApplicationFiled: November 28, 2016Publication date: March 16, 2017Inventors: Andrew Maresh, Frank Bradley Stamps, Patrick Ryan Tisdale, Robert Patrick Wardlaw, Andrew Haldeman, Drew Alan Sutton
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Patent number: 9505490Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.Type: GrantFiled: March 13, 2013Date of Patent: November 29, 2016Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Maresh, Frank Bradley Stamps, Patrick Ryan Tisdale, Robert Wardlaw, Andrew Haldeman, Drew Sutton
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Publication number: 20160280367Abstract: A rotor blade assembly includes a rotor blade comprising an inboard end and an outboard end. A composite yoke fitting made from a composite material is attached to the rotor blade. The composite yoke fitting includes an outboard portion inserted into the inboard end of the rotor blade, an inboard portion, and a flexure region about which the rotor blade is configured to flex. The inboard portion and the flexure region are outside the rotor blade.Type: ApplicationFiled: March 26, 2015Publication date: September 29, 2016Inventors: Andrew Haldeman, Frank Bradley Stamps, Drew Sutton
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Publication number: 20140271180Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.Type: ApplicationFiled: March 13, 2013Publication date: September 18, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Haldeman, Frank Bradley Stamps, Drew Sutton, James Donn Hethcock
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Publication number: 20140271214Abstract: A rotor blade abrasion strip and method to manufacturing the same. The abrasion strip being composed of a molded amorphous metal contoured to match a leading edge outer surface of the rotor blade. The abrasion strip being configured to removably attach to a leading edge of the rotor blade and configured to prevent damage to the leading edge during flight. The method includes molding the abrasion strip with the amorphous metal.Type: ApplicationFiled: March 14, 2013Publication date: September 18, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Drew Sutton, Jeffrey P. Nissen, Andrew Haldeman
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Publication number: 20140271222Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.Type: ApplicationFiled: March 13, 2013Publication date: September 18, 2014Inventors: Andrew Maresh, Frank Bradley Stamps, Patrick Ryan Tisdale, Robert Wardlaw, Andrew Haldeman, Drew Sutton