Patents by Inventor Larry J. Ashton
Larry J. Ashton 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: 7963482Abstract: A cabin door assembly is provided for use with a pressurized aircraft. The assembly includes two door halves for engaging the fuselage of the aircraft. Structurally, each door half includes a waist section integral with an adjoining tapered section. Further, the assembly includes an activator that is mounted on the fuselage and attached to the door halves. Specifically, the activator is attached to each door half to concertedly move each door half between a closed configuration and an open configuration. In the closed configuration, the door halves are sealed to the fuselage and to each other for pressurization of the aircraft. In the open configuration, the door halves extend outwardly from the fuselage to allow for aircraft ingress and egress.Type: GrantFiled: February 4, 2008Date of Patent: June 21, 2011Assignee: Spectrum Aeronautical, LLCInventors: Larry J. Ashton, Kendall J. Fowkes, Michael G. Allman
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Patent number: 7850897Abstract: A method and device are provided for manufacturing a unitary caul sheet to be used in creating a composite material fuselage for an airplane. Specifically, a generally tubular shaped tool having a hollow interior cavity defining a fuselage IML surface is provided. In the method, a caul sheet material such as polyurea is applied to the IML surface before an armature is inserted into the interior cavity of the tool. Then, a filler material is introduced between the armature and the caul sheet material. Further, steam is injected to form the filler material into an infrastructure. Then, the caul sheet material is cured before the tool is removed from the caul sheet material to expose the caul sheet to receive composite material.Type: GrantFiled: March 14, 2007Date of Patent: December 14, 2010Assignee: Spectrum Aeronautical, LLCInventors: Larry J. Ashton, William T. McCarvill
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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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Patent number: 7681835Abstract: A single piece co-cured composite wing is disclosed. The wing has a flying surface and structural members. In one embodiment the structural members may be a plurality of spars. The spars may have various shapes to increase the buckling strength. The spars may be wave shaped, such as a sinusoidal shape. The flying surface and the structural members are co-cured in order to form a single piece, integral wing structure. A process for manufacturing a single piece co-cured wing is also disclosed. The process may include laying out composite sheets for the flying surface of the wing. Then, the composite material of the spars is arranged around a plurality of pressurizable forms. Finally, the composite material is cured in a clamshell frame. A single piece co-cured composite structure is also disclosed that includes an outer skin, and inner skin, a frame, and a stringer.Type: GrantFiled: September 23, 2005Date of Patent: March 23, 2010Assignee: Rocky Mountain Composites, Inc.Inventors: Craig B. Simpson, Larry J. Ashton, Mike G. Allman, Steven T. Tuttle
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Publication number: 20090194637Abstract: A cabin door assembly is provided for use with a pressurized aircraft. The assembly includes two door halves for engaging the fuselage of the aircraft. Structurally, each door half includes a waist section integral with an adjoining tapered section. Further, the assembly includes an activator that is mounted on the fuselage and attached to the door halves. Specifically, the activator is attached to each door half to concertedly move each door half between a closed configuration and an open configuration. In the closed configuration, the door halves are sealed to the fuselage and to each other for pressurization of the aircraft. In the open configuration, the door halves extend outwardly from the fuselage to allow for aircraft ingress and egress.Type: ApplicationFiled: February 4, 2008Publication date: August 6, 2009Inventors: Larry J. Ashton, Kendall J. Fowkes, Michael G. Allman
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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: 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: 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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Patent number: 7445744Abstract: A single piece co-cured composite wing is disclosed. The wing has a flying surface and structural members. In one embodiment the structural members may be a plurality of spars. The spars may have various shapes to increase the buckling strength. The spars may be wave shaped, such as a sinusoidal shape. The flying surface and the structural members are co-cured in order to form a single piece, integral wing structure. A process for manufacturing a single piece co-cured wing is also disclosed. The process may include laying out composite sheets for the flying surface of the wing. Then, the composite material of the spars is arranged around a plurality of pressurizable forms. Finally, the composite material is cured in a clamshell frame.Type: GrantFiled: December 3, 2003Date of Patent: November 4, 2008Assignee: Rocky Mountain Composites, Inc.Inventors: Craig B. Simpson, Mike Glen Allman, Steven Taylor Tuttle, Larry J. Ashton
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Publication number: 20080224360Abstract: A method and device are provided for manufacturing a unitary caul sheet to be used in creating a composite material fuselage for an airplane. Specifically, a generally tubular shaped tool having a hollow interior cavity defining a fuselage IML surface is provided. In the method, a caul sheet material such as polyurea is applied to the IML surface before an armature is inserted into the interior cavity of the tool. Then, a filler material is introduced between the armature and the caul sheet material. Further, steam is injected to form the filler material into an infrastructure. Then, the caul sheet material is cured before the tool is removed from the caul sheet material to expose the caul sheet to receive composite material.Type: ApplicationFiled: March 14, 2007Publication date: September 18, 2008Inventors: Larry J. Ashton, William T. McCarvill
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Patent number: 7216832Abstract: A method for manufacturing a composite structure is disclosed herein. The process uses a frame and selectively pressurizable forms. The forms define the interior members of the composite structure and frames define the exterior surface of the composite structure. Composite material is wrapped around the forms and the forms and composite material are placed in the frame. Selective forms are then pressurized and the composite material is co-cured together. A single piece co-cured fuselage incorporating a plurality of stiffeners is also disclosed in the application. The stiffeners are co-cured to the fuselage and may be in various patterns. The patterns may include an iso-grid pattern, and ortho-grid pattern, and a hoop-grid pattern.Type: GrantFiled: December 1, 2004Date of Patent: May 15, 2007Assignee: Rocky Mountain Composites, Inc.Inventors: Craig B. Simpson, Mike G. Allman, Steven T. Tuttle, Larry J. Ashton
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Patent number: 7204951Abstract: A method for manufacturing a composite structure is disclosed herein. The process uses a frame and selectively pressurizable forms. The forms define the interior members of the composite structure and frames define the exterior surface of the composite structure. Composite material is wrapped around the forms and the forms and composite material are placed in the frame. Selective forms are then pressurized and the composite material is co-cured together. A single piece co-cured fuselage incorporating a plurality of stiffeners is also disclosed in the application. The stiffeners are co-cured to the fuselage and may be in various patterns. The patterns may include an iso-grid pattern, and ortho-grid pattern, and a hoop-grid pattern.Type: GrantFiled: July 30, 2002Date of Patent: April 17, 2007Assignee: Rocky Mountain Composites, Inc.Inventors: Craig B. Simpson, Mike G. Allman, Steven T. Tuttle, Larry J. Ashton
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Patent number: 6904873Abstract: A fuel-fired boiler having a supply fan for providing essentially all of its combustion air requirements and has a non-aspirating type burner section to an inlet portion of which pressure regulator apparatus is coupled, the pressure regulator apparatus having a predetermined pressure regulation setting. Fuel delivery apparatus is coupled to the inlet of the pressure regulator apparatus and is operative to deliver thereto, from sources thereof, a selectively variable one of (1) a first fuel at a pressure greater than the pressure regulation setting, and (2) a second fuel at a pressure less than the pressure regulation setting, the second fuel having a Wobbe index greater than that of the first fuel. The design of the fuel delivery apparatus permits the burner section firing rate to remain essentially constant, without modifying the burner section, regardless of which of the two fuels is being utilized.Type: GrantFiled: January 20, 2004Date of Patent: June 14, 2005Assignee: Rheem Manufacturing CompanyInventor: Larry J. Ashton
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Patent number: 6889937Abstract: A single piece co-cured composite wing is disclosed. The wing has a flying surface and structural members. In one embodiment the structural members may be a plurality of spars. The spars may have various shapes to increase the buckling strength. The spars may be wave shaped, such as a sinusoidal shape. The flying surface and the structural members are co-cured in order to form a single piece, integral wing structure. A process for manufacturing a single piece co-cured wing is also disclosed. The process may include laying out composite sheets for the flying surface of the wing. Then, the composite material of the spars is arranged around a plurality of pressurizable forms. Finally, the composite material is cured in a clamshell frame.Type: GrantFiled: June 20, 2002Date of Patent: May 10, 2005Assignee: Rocky Mountain Composites, Inc.Inventors: Craig B. Simpson, Mike Glen Allman, Steven Taylor Tuttle, Larry J. Ashton