Patents by Inventor John R. McCullough
John R. McCullough 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: 10180151Abstract: An apparatus for attaching a member to a honeycomb core-stiffened structure includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of a honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus. A honeycomb core-stiffened structure includes a honeycomb core and an apparatus for attaching a member to the honeycomb core. The apparatus includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of the honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus.Type: GrantFiled: November 2, 2015Date of Patent: January 15, 2019Assignee: Textron Innovations Inc.Inventors: Carl A. May, James D. Hethcock, Jr., John R. McCullough, Ronald K. Cox
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Publication number: 20180297685Abstract: An aircraft includes a composite structure, comprising an outer skin formed from a composite material and having a first thickness, an inner skin formed from a composite material and having a second thickness, the second thickness being greater than the first thickness, and a core structure positioned between the inner and outer skins to increase bending stiffness of the composite structure. During use a structural load carried by the inner skin exceeds a structural load carried by the outer skin.Type: ApplicationFiled: April 14, 2017Publication date: October 18, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Carl May, James D. Hethcock, JR., John R. McCullough
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Patent number: 10059064Abstract: An apparatus comprising a soft in plane rotor yoke comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material having a plurality of first fibers oriented in a first direction, and a plurality of second layers formed of a second composite fabric material having a plurality of second fibers oriented in a second direction. Included is an apparatus comprising a soft in plane rotor comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material, and a plurality of second layers formed of a second composite fabric material, wherein the soft in plane rotor yoke does not comprise any narrow steered slit tape or filament windings.Type: GrantFiled: June 16, 2017Date of Patent: August 28, 2018Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Robert Wardlaw, Werner Idler, John R. McCullough, Patrick Ryan Tisdale, Frank Bradley Stamps, James L. Braswell, Jr., Ronald J. Measom, Paul K. Oldroyd
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Publication number: 20180141246Abstract: A composite structure includes a first face sheet, a second face sheet, and a foam member located between the first face sheet and the second face sheet. The foam member has a molded contour, the mold contour being configured to provide tooling surface for at least one of the first face sheet and the second face sheet prior to curing of the composite structure. A method of making the foam member includes creating a mold tool having an interior surface which resembles the desired outer contour of the foam member. A mixture is poured into a pour opening in the mold tool. The mixture is allowed to polymerize into a foam as the foam expands and distributes within the mold tool. Vent openings in the mold tool are selectively tailored to control the density of the foam member. The foam member is cured in the mold tool.Type: ApplicationFiled: January 16, 2018Publication date: May 24, 2018Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Suvankar Mishra, John R. McCullough, Mark Chris, Stanley B. Woychesin
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Patent number: 9868233Abstract: A composite structure includes a first face sheet, a second face sheet, and a foam member located between the first face sheet and the second face sheet. The foam member has a molded contour, the mold contour being configured to provide tooling surface for at least one of the first face sheet and the second face sheet prior to curing of the composite structure. A method of making the foam member includes creating a mold tool having an interior surface which resembles the desired outer contour of the foam member. A mixture is poured into a pour opening in the mold tool. The mixture is allowed to polymerize into a foam as the foam expands and distributes within the mold tool. Vent openings in the mold tool are selectively tailored to control the density of the foam member. The foam member is cured in the mold tool.Type: GrantFiled: July 15, 2011Date of Patent: January 16, 2018Assignee: Textron Innovations Inc.Inventors: Suvankar Mishra, John R. McCullough, Mark Chris, Stanley B. Woychesin
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Publication number: 20180001590Abstract: In one aspect, there is a method of making a composite skin for a tiltrotor aircraft including providing a first skin in a mold, the first skin having a periphery defined by a forward edge, an aft edge, and outboard ends; providing a plurality of honeycomb panels having an array of large cells onto the first skin, each cell having a width of at least 1 cm; assembling the plurality of honeycomb panels along the longitudinal axis of the first skin to form a honeycomb core having an outer perimeter within the periphery of the first skin; positioning a second skin onto the honeycomb core, the second skin having an outer perimeter within the periphery of the first skin; and curing an adhesive to create a bond between the first skin, the honeycomb core, and the second skin to form a composite skin.Type: ApplicationFiled: February 3, 2017Publication date: January 4, 2018Applicant: Bell Helicopter Textron Inc.Inventors: David G. Carlson, John R. McCullough, Douglas K. Wolfe, Andrew G. Baines, George R. Decker
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Publication number: 20180001579Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold, the mold having a periphery defined by a forward edge, an aft edge, and outboard ends. The method includes selecting a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies; laying the plies in a mold; compacting the plies in a mold; and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery of the mold. In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies.Type: ApplicationFiled: February 3, 2017Publication date: January 4, 2018Applicant: Bell Helicopter Textron Inc.Inventors: David G. Carlson, John R. McCullough, Douglas K. Wolfe, Andrew G. Baines, George R. Decker
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Publication number: 20170291701Abstract: An apparatus comprising a soft in plane rotor yoke comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material having a plurality of first fibers oriented in a first direction, and a plurality of second layers formed of a second composite fabric material having a plurality of second fibers oriented in a second direction. Included is an apparatus comprising a soft in plane rotor comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material, and a plurality of second layers formed of a second composite fabric material, wherein the soft in plane rotor yoke does not comprise any narrow steered slit tape or filament windings.Type: ApplicationFiled: June 16, 2017Publication date: October 12, 2017Inventors: Robert Wardlaw, Werner Idler, John R. McCullough, Patrick Ryan Tisdale, Frank Bradley Stamps, James L. Braswell, JR., Ronald J. Measom, Paul K. Oldroyd
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Publication number: 20170225769Abstract: A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold; and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold using a tool positioned in the plurality of bores.Type: ApplicationFiled: February 3, 2017Publication date: August 10, 2017Applicant: Bell Helicopter Textron Inc.Inventors: David G. Carlson, John R. McCullough, Douglas K. Wolfe, George R. Decker, Keith A. Stanney
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Publication number: 20170225766Abstract: In one aspect, there is a rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.Type: ApplicationFiled: February 3, 2017Publication date: August 10, 2017Applicant: Bell Helicopter Textron Inc.Inventors: David G. Carlson, John R. McCullough, Paul K. Oldroyd, Carl A. May, James E. Kooiman
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Publication number: 20170225765Abstract: In one aspect, there is provided a spar member for an aircraft wing including a support beam having an interior surface, an exterior surface, and opposing ends configured for an aircraft wing, the interior surface and exterior surface disposed between the opposing ends; and a first spar flange extending generally laterally from the exterior surface, the first spar flange configured for attachment with a first wing skin. The first spar flange can be an upper or lower spar flange. In some embodiments, the first spar flange is at an acute angle relative to the exterior surface of the support beam. In certain embodiments, the first spar flange is at an angle of from about 50 degrees to about 85 degrees relative to the exterior surface of the support beam.Type: ApplicationFiled: February 3, 2017Publication date: August 10, 2017Applicant: Bell Helicopter Textron Inc.Inventors: Douglas K. Wolfe, David G. Carlson, John R. McCullough, George R. Decker
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Patent number: 9714086Abstract: An apparatus comprising a soft in plane rotor yoke comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material having a plurality of first fibers oriented in a first direction, and a plurality of second layers formed of a second composite fabric material having a plurality of second fibers oriented in a second direction. Included is an apparatus comprising a soft in plane rotor comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material, and a plurality of second layers formed of a second composite fabric material, wherein the soft in plane rotor yoke does not comprise any narrow steered slit tape or filament windings.Type: GrantFiled: March 13, 2013Date of Patent: July 25, 2017Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Robert Wardlaw, Werner Idler, John R. McCullough, Patrick Ryan Tisdale, Frank Bradley Stamps, James L. Braswell, Jr., Ronald J. Measom, Paul K. Oldroyd
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Patent number: 9592901Abstract: A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.Type: GrantFiled: January 12, 2015Date of Patent: March 14, 2017Assignee: Textron Innovations Inc.Inventors: John R. McCullough, David Gordon Carlson, James Donn Hethcock, Paul K. Oldroyd, Carl A. May
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Patent number: 9550334Abstract: A method of repairing a core stiffened structure can include removing a damaged portion of the core stiffened structure; creating a cutout in a portion of a repair core member; fitting the repair core member onto an existing core member such that the cutout mates with a portion of the existing core member; bonding the repair core member to the existing core member; and placing a skin patch over the repair core member.Type: GrantFiled: September 25, 2014Date of Patent: January 24, 2017Inventors: Suvankar Mishra, Jesse Wrabel, John R. McCullough, Randall Willnow, Carl May
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Publication number: 20160300003Abstract: A method of performing structural analysis relating to a component having CAD-based geometry, refined CAD-based geometry and CAD-based FEA data associated therewith. The method includes scanning the component to obtain scan-based point cloud geometry of the component, aligning the scan-based point cloud geometry with the CAD-based geometry of the component, generating scan-based geometry of the component by refining the scan-based point cloud geometry, comparing the scan-based geometry with the refined CAD-based geometry of the component to quantify geometric differences therebetween, generating scan-based FEA geometry of the component by meshing the scan-based geometry, performing finite element analysis on the scan-based FEA geometry to obtain scan-based FEA data and comparing the scan-based FEA data with the CAD-based FEA data of the component to quantify the effect of geometric difference therebetween.Type: ApplicationFiled: April 7, 2016Publication date: October 13, 2016Applicant: Bell Helicopter Textron Inc.Inventors: Jonathan A. Knoll, Jeffrey P. Nissen, John R. McCullough
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Patent number: 9333684Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: GrantFiled: October 30, 2012Date of Patent: May 10, 2016Assignee: Bell Helicopter Textron Inc.Inventors: Ramesh Thiagarajan, Robert Mark Chris, John R. McCullough, Suvankar Mishra
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Publication number: 20160089844Abstract: A method of repairing a core stiffened structure can include removing a damaged portion of the core stiffened structure; creating a cutout in a portion of a repair core member; fitting the repair core member onto an existing core member such that the cutout mates with a portion of the existing core member; bonding the repair core member to the existing core member; and placing a skin patch over the repair core member.Type: ApplicationFiled: September 25, 2014Publication date: March 31, 2016Inventors: Suvankar Mishra, Jesse Wrabel, John R. McCullough, Randall Willnow, Carl May
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Publication number: 20160053785Abstract: An apparatus for attaching a member to a honeycomb core-stiffened structure includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of a honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus. A honeycomb core-stiffened structure includes a honeycomb core and an apparatus for attaching a member to the honeycomb core. The apparatus includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of the honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus.Type: ApplicationFiled: November 2, 2015Publication date: February 25, 2016Applicant: BELL HELICOPTER TEXTRON INC.Inventors: CARL A. MAY, JAMES D. HETHCOCK, JR., JOHN R. MCCULLOUGH, RONALD K. COX
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Patent number: 9193454Abstract: In accordance with one embodiment of the present disclosure, a trunnion includes a first portion and a second portion. The first portion is capable of coupling directly to a drive tube of an aircraft, wherein the drive tube is capable of rotating around a first axis. The second portion is capable of coupling to a swash plate of the aircraft, wherein the swash plate is capable of causing the pitch of at least one of a plurality of aircraft blades to change.Type: GrantFiled: October 24, 2012Date of Patent: November 24, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Brian S. Modrzejewski, Gary D. Hall, John R. McCullough, Farid Saiyed, Glenn A. Shimek, Danny A. Spivey, Tim Stark, Brian S. Vollmer
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Patent number: 9174731Abstract: A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member.Type: GrantFiled: August 14, 2013Date of Patent: November 3, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Brent C. Ross, David R. Bockmiller, John R. McCullough, David G. Carlson