Patents by Inventor Michael G. Allman
Michael G. Allman 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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Publication number: 20240165499Abstract: Dice which have the exterior form of regular polyhedrons, but are not solid polyhedrons. Instead, the dice, when viewed externally, are in the form of skeletal polyhedrons with floating faces. The dice also include a solid core surrounding their center which can serve to improve tumbling behavior.Type: ApplicationFiled: November 22, 2022Publication date: May 23, 2024Inventors: Tyson J. Lauby, Michael G. Allman
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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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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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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: 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: 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: 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: 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: 5467889Abstract: A fuel tank for aircraft includes a rigid securement for securing the tank to the aircraft, a skin connected to the securement, and a liner inside the skin. The skin includes an elastic fiber and a tensile fiber embedded in a flexible matrix. In one embodiment, the elastic fiber and the tensile fiber are wound in layers within the flexible matrix, and the elastic fiber is wrapped spirally about the tensile fiber. The elastic fiber is preferably an elastomeric fiber such as an elastic, segmented polyurethane fiber. The tensile fiber is preferably an aramid polymer fiber such as an aromatic polycarbonamide fiber. The flexible matrix may be formed of natural rubber or neoprene rubber. When the tank is filled, the elastic fiber lengthens until the tensile fiber resists further stretching. The elastic fiber tends to contract as the tank is emptied, substantially reducing the storage space required by the tank. The tank is nestable when empty, but is nonetheless substantially ready to receive fuel.Type: GrantFiled: July 12, 1994Date of Patent: November 21, 1995Assignee: AeroTransInventors: Larry J. Ashton, Michael G. Allman, Benko Ta-Ala