Patents by Inventor Ian C. Burford
Ian C. Burford 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: 10793251Abstract: Hinge pins for foldable aircraft wings are described. An example apparatus includes a hinge pin to rotatably couple a foldable tip of an aircraft wing to a fixed structure of the aircraft wing. The hinge pin includes a first flange, a second flange spaced apart from the first flange along a central axis of the hinge pin, and a through hole oriented along the central axis.Type: GrantFiled: March 22, 2018Date of Patent: October 6, 2020Assignee: THE BOEING COMPANYInventors: Eric S. Kamila, Warren H. Steyaert, David D. Boes, Daniel E. McGinty, Ryan A. Fear, Renato Felicio, Eric G. Gruner, Matthew S. Elenbaas, Ian C. Burford, Eric D. Blohm
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Publication number: 20190291847Abstract: Hinge pins for foldable aircraft wings are described. An example apparatus includes a hinge pin to rotatably couple a foldable tip of an aircraft wing to a fixed structure of the aircraft wing. The hinge pin includes a first flange, a second flange spaced apart from the first flange along a central axis of the hinge pin, and a through hole oriented along the central axis.Type: ApplicationFiled: March 22, 2018Publication date: September 26, 2019Inventors: Eric S. Kamila, Warren H. Steyaert, David D. Boes, Daniel E. McGinty, Ryan A. Fear, Renato Felicio, Eric G. Gruner, Matthew S. Elenbaas, Ian C. Burford, Eric D. Blohm
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Patent number: 9073618Abstract: A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.Type: GrantFiled: May 2, 2013Date of Patent: July 7, 2015Assignee: The Boeing CompanyInventors: Richard B. Tanner, Brian H. Korenaga, Jeffrey F. Stulc, Ian C. Burford
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Publication number: 20130232883Abstract: A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.Type: ApplicationFiled: May 2, 2013Publication date: September 12, 2013Applicant: The Boeing CompanyInventors: Richard B. Tanner, Brian H. Korenaga, Jeffrey F. Stulc, Ian C. Burford
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Patent number: 8443575Abstract: A door for an aircraft wing fuel tank access opening includes an outer impact resistant composite door panel, and an inner composite door panel. Double seals on the inner door panel prevent fuel leakage, and a chamfered outer edge on the outer door panel transfers a component of impact loads laterally into the wing skin to increase kinetic energy absorption.Type: GrantFiled: October 27, 2009Date of Patent: May 21, 2013Assignee: The Boeing CompanyInventors: Richard B Tanner, Brian H. Korenaga, Jeffrey F Stulc, Ian C Burford
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Patent number: 7721995Abstract: An innovative wing structure provides fibs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an āIā section and is stable under compression, not requiring mechanical methods to prevent rolling over.Type: GrantFiled: December 13, 2006Date of Patent: May 25, 2010Assignee: The Boeing CompanyInventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga
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Patent number: 7686251Abstract: A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.Type: GrantFiled: October 4, 2007Date of Patent: March 30, 2010Assignee: The Boeing CompanyInventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga
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Patent number: 7628358Abstract: A wing panel structure for an aerospace vehicle or the like may include an outer layer of material having a predetermined thickness. A core structure may be placed on at least a portion of the outer layer of material. An inner layer of material may be placed at least on the core structure. The inner layer of material may have a selected thickness less than the predetermined thickness of the outer layer of material.Type: GrantFiled: October 26, 2006Date of Patent: December 8, 2009Assignee: The Boeing CompanyInventors: James F. Ackermann, Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill
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Publication number: 20080210821Abstract: An innovative wing structure provides ribs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an āIā section and is stable under compression, not requiring mechanical methods to prevent rolling over.Type: ApplicationFiled: December 13, 2006Publication date: September 4, 2008Applicant: THE BOEING COMPANYInventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga
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Publication number: 20080173757Abstract: A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.Type: ApplicationFiled: October 4, 2007Publication date: July 24, 2008Inventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga
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Patent number: 7387277Abstract: Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.Type: GrantFiled: December 29, 2004Date of Patent: June 17, 2008Assignee: The Boeing CompanyInventors: Jan A. Kordel, Richard B. Tanner, Ian C. Burford, Victor A. Munsen, Daniel E. McGinty, Scott N. Rampton, Bruce R. Fox, James M. Kelly, Miles O. Johnson
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Publication number: 20080099613Abstract: A wing panel structure for an aerospace vehicle or the like may include an outer layer of material having a predetermined thickness. A core structure may be placed on at least a portion of the outer layer of material. An inner layer of material may be placed at least on the core structure. The inner layer of material may have a selected thickness less than the predetermined thickness of the outer layer of material.Type: ApplicationFiled: October 26, 2006Publication date: May 1, 2008Inventors: James F. Ackermann, Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill
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Publication number: 20080023585Abstract: Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.Type: ApplicationFiled: December 29, 2004Publication date: January 31, 2008Inventors: Jan A. Kordel, Richard B. Tanner, Ian C. Burford, Victor A. Munsen, Daniel E. McGinty, Scott N. Rampton, Bruce R. Fox, James M. Kelly, Miles O. Johnson