Patents by Inventor Troy L. White
Troy L. White 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: 9623610Abstract: A method for manufacturing rigid panels made of a composite material requires a caul sheet having a smooth surface that is formed with a plurality of grooves. A first layer of the composite material is laid on the caul sheet, and is cut to create flaps that extend into the respective grooves. Strips of composite material are then placed along the edges of the groove to extend and overlap each other in the groove. Next, a unidirectional ply is placed along the length of the groove, and this combination is then covered with a second layer of the composite material. Together, the combination of the first and second layers, the strips and the unidirectional ply are co-cured to create a rigid panel with integral stiffening members.Type: GrantFiled: January 24, 2014Date of Patent: April 18, 2017Assignee: Spectrum Aeronautical, LLCInventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Benko S. Ta'ala
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Patent number: 9610756Abstract: A composite material made of multiple filament bands is disclosed. The filament bands are wound to create a composite material. The filament bands may be impregnated with a solid or semi-solid resin. The filament bands are wound in multiple orientations to form a sheet of composite material. Additionally, the composite material may be made to have a varying number of layer and fiber orientations throughout the sheet of composite material. In another embodiment, a composite component requiring multiple layers and fiber orientations may be substantially manufactured during a filament winding process.Type: GrantFiled: February 25, 2013Date of Patent: April 4, 2017Assignee: ROCKY MOUNTAIN COMPOSITES, INC.Inventors: Larry J. Ashton, Craig B. Simpson, Rex W. Kay, Troy L. White, Mike Glen Allman
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Publication number: 20140138873Abstract: A method for manufacturing rigid panels made of a composite material requires a caul sheet having a smooth surface that is formed with a plurality of grooves. A first layer of the composite material is laid on the caul sheet, and is cut to create flaps that extend into the respective grooves. Strips of composite material are then placed along the edges of the groove to extend and overlap each other in the groove. Next, a unidirectional ply is placed along the length of the groove, and this combination is then covered with a second layer of the composite material. Together, the combination of the first and second layers, the strips and the unidirectional ply are co-cured to create a rigid panel with integral stiffening members.Type: ApplicationFiled: January 24, 2014Publication date: May 22, 2014Applicant: Spectrum Aeronautical, LLCInventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Benko S. Ta'ala
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Patent number: 8668858Abstract: A method for manufacturing rigid panels made of a composite material requires a caul sheet having a smooth surface that is formed with a plurality of grooves. A first layer of the composite material is laid on the caul sheet, and is cut to create flaps that extend into the respective grooves. Strips of composite material are then placed along the edges of the groove to extend and overlap each other in the groove. Next, a unidirectional ply is placed along the length of the groove, and this combination is then covered with a second layer of the composite material. Together, the combination of the first and second layers, the strips and the unidirectional ply are co-cured to create a rigid panel with integral stiffening members.Type: GrantFiled: September 14, 2007Date of Patent: March 11, 2014Assignee: Spectrum Aeronautical, LLCInventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Benko S. Ta'ala
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Publication number: 20130164491Abstract: A composite material made of multiple filament bands is disclosed. The filament bands are wound to create a composite material. The filament bands may be impregnated with a solid or semi-solid resin. The filament bands are wound in multiple orientations to form a sheet of composite material. Additionally, the composite material may be made to have a varying number of layer and fiber orientations throughout the sheet of composite material. In another embodiment, a composite component requiring multiple layers and fiber orientations may be substantially manufactured during a filament winding process.Type: ApplicationFiled: February 25, 2013Publication date: June 27, 2013Inventors: Larry J. Ashton, Craig B. Simpson, Rex W. Kay, Troy L. White, Mike Glen Allman
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Patent number: 8042315Abstract: A reinforced panel, made of a composite material, includes a single base layer. A first plurality of mutually parallel ridges is affixed to the surface of the base layer. A second plurality of mutually parallel ridges is also affixed to the surface of the base layer, but oriented transverse to the first plurality. Structurally, the ridges and the base layer are co-cured to create an integral, continuous structure that provides stiffness and rigidity to the panel.Type: GrantFiled: September 14, 2007Date of Patent: October 25, 2011Assignee: Spectrum Aeronautical, LLCInventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Craig B. Simpson, Benko S. Ta'ala
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Patent number: 7828246Abstract: An aircraft wing made of a composite material, and its method of manufacture, require a plurality of kabobs (i.e. substantially rectangular shaped hollow tubes having an open end and a closed end). Of these kabobs, several are aligned end-to-end, to create a section. Several sections are then positioned side-by-side and covered by a layer of composite material to define an aerodynamic surface for the wing. The juxtaposed sections also establish spar webs for the wing, and the closed ends of the juxtaposed sections establish transverse ribs for the wing. Thus, the kabobs form the main load-bearing member of the wing. The sections of composite material are co-cured with the composite material of the aerodynamic surface.Type: GrantFiled: September 14, 2007Date of Patent: November 9, 2010Assignee: Spectrum Aeronautical, LLCInventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Danny L. Stark
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Publication number: 20090072429Abstract: A method for manufacturing rigid panels made of a composite material requires a caul sheet having a smooth surface that is formed with a plurality of grooves. A first layer of the composite material is laid on the caul sheet, and is cut to create flaps that extend into the respective grooves. Strips of composite material are then placed along the edges of the groove to extend and overlap each other in the groove. Next, a unidirectional ply is placed along the length of the groove, and this combination is then covered with a second layer of the composite material. Together, the combination of the first and second layers, the strips and the unidirectional ply are co-cured to create a rigid panel with integral stiffening members.Type: ApplicationFiled: September 14, 2007Publication date: March 19, 2009Inventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Benko S. Ta'ala
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Publication number: 20090071098Abstract: A reinforced panel, made of a composite material, includes a single base layer. A first plurality of mutually parallel ridges is affixed to the surface of the base layer. A second plurality of mutually parallel ridges is also affixed to the surface of the base layer, but oriented transverse to the first plurality. Structurally, the ridges and the base layer are co-cured to create an integral, continuous structure that provides stiffness and rigidity to the panel.Type: ApplicationFiled: September 14, 2007Publication date: March 19, 2009Inventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Craig B. Simpson, Benko S. Ta'ala
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Publication number: 20090072088Abstract: An aircraft wing made of a composite material, and its method of manufacture, require a plurality of kabobs (i.e. substantially rectangular shaped hollow tubes having an open end and a closed end). Of these kabobs, several are aligned end-to-end, to create a section. Several sections are then positioned side-by-side and covered by a layer of composite material to define an aerodynamic surface for the wing. The juxtaposed sections also establish spar webs for the wing, and the closed ends of the juxtaposed sections establish transverse ribs for the wing. Thus, the kabobs form the main load-bearing member of the wing. The sections of composite material are co-cured with the composite material of the aerodynamic surface.Type: ApplicationFiled: September 14, 2007Publication date: March 19, 2009Inventors: Larry J. Ashton, Michael G. Allman, Troy L. White, Danny L. Stark
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Publication number: 20040074592Abstract: A composite material made of multiple filament bands is disclosed. The filament bands are wound to create a composite material. The filament bands may be impregnated with a solid or semi-solid resin. The filament bands are wound in multiple orientations to form a sheet of composite material. Additionally, the composite material may be made to have a varying number of layer and fiber orientations throughout the sheet of composite material. In another embodiment, a composite component requiring multiple layers and fiber orientations may be substantially manufactured during a filament winding process.Type: ApplicationFiled: October 14, 2003Publication date: April 22, 2004Inventors: Larry J. Ashton, Craig B. Simpson, Rex W. Kay, Troy L. White, Mike Glen Allman
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Publication number: 20030186038Abstract: A composite material made of multiple filament bands is disclosed. The filament bands are wound to create a composite material. The filament bands may be impregnated with a solid or semi-solid resin. The filament bands are wound in multiple orientations to form a sheet of composite material. Additionally, the composite material may be made to have a varying number of layer and fiber orientations throughout the sheet of composite material. In another embodiment, a composite component requiring multiple layers and fiber orientations may be substantially manufactured during a filament winding process.Type: ApplicationFiled: June 20, 2002Publication date: October 2, 2003Inventors: Larry J. Ashton, Craig B. Simpson, Rex W. Kay, Troy L. White, Mike Glen Allman
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Patent number: 6482497Abstract: A method and apparatus for manufacturing fiber-reinforced, composite materials relies on one or more processes improving over conventional forming, filling, and processing techniques. A homogeneous resin-stitching process provides for resin stitching for using only 5-20 percent of the rovings in a preform as wetted rovings, cured to maintain a stitching together of the structure. A resin-packet transfer process provides infusion of resins from directly beside a wall of a preform, rather than passing resins throughout the longitudinal length of fibers in a perform. A cyclic vacuum bagging process alternately applied over pressure and outside vacuum to a vacuum bag process, thus relieving pressure, and later, optionally, applying pressure to improve structural strength. Relieving pressure tends to improve (reduce) porosity.Type: GrantFiled: November 18, 1999Date of Patent: November 19, 2002Assignee: Rocky Mountain Composites Inc.Inventors: Rex W. Kay, Troy L. White, Craig B. Simpson