Patents by Inventor Jeff D. Will
Jeff D. Will 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: 9394062Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.Type: GrantFiled: March 26, 2015Date of Patent: July 19, 2016Assignee: THE BOEING COMPANYInventors: Brad L. Kirkwood, Paul S. Gregg, Gerald D. Miller, Jeff D. Will, David W. Evans
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Publication number: 20150259079Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.Type: ApplicationFiled: March 26, 2015Publication date: September 17, 2015Inventors: Brad L. Kirkwood, Paul S. Gregg, Gerald D. Miller, Jeff D. Will, David W. Evans
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Patent number: 9016551Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.Type: GrantFiled: November 2, 2006Date of Patent: April 28, 2015Assignee: The Boeing CompanyInventors: Brad L. Kirkwood, Paul S. Gregg, Gerry D. Miller, Jeff D. Will, David W. Evans
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Patent number: 8329312Abstract: A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.Type: GrantFiled: June 27, 2011Date of Patent: December 11, 2012Assignee: The Boeing CompanyInventors: Daniel G. Sanders, David W. Foutch, Jeff D. Will, Luis Leon, Gregory L. Ramsey, Garry A. Booker
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Publication number: 20110256343Abstract: A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.Type: ApplicationFiled: June 27, 2011Publication date: October 20, 2011Applicant: The Boeing CompanyInventors: Daniel G. Sanders, David W. Foutch, Jeff D. Will, Luis Leon, Gregory L. Ramsey, Garry A. Booker
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Patent number: 7967240Abstract: A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.Type: GrantFiled: March 16, 2007Date of Patent: June 28, 2011Assignee: The Boeing CompanyInventors: Daniel G. Sanders, David W. Foutch, Jeff D. Will, Luis Leon, Gregory L. Ramsey, Garry A. Booker
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Patent number: 7818945Abstract: Composite structural members and methods for forming the same are disclosed. In one embodiment, a composite structural member includes a central structural portion that extends in a first direction and having a first flange portion and a second flange portion that are spaced apart in a second direction perpendicular to the first direction by a web portion, the web portion further including a periodic or a non-periodic undulation extending in the first direction. A first reinforced polymer-based substrate is fixedly coupled to the first flange portion, and a second reinforced polymer-based substrate is fixedly coupled to the second flange portion.Type: GrantFiled: September 29, 2006Date of Patent: October 26, 2010Assignee: The Boeing CompanyInventors: Paul S. Gregg, Max U. Kismarton, Jeff D. Will
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Patent number: 7810757Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.Type: GrantFiled: November 2, 2006Date of Patent: October 12, 2010Assignee: The Boeing CompanyInventors: Brad L Kirkwood, Paul S. Gregg, Gerald D. Miller, Jeff D. Will, David W. Evans
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Publication number: 20100162567Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.Type: ApplicationFiled: November 2, 2006Publication date: July 1, 2010Applicant: THE BOEING COMPANYInventors: Brad L. Kirkwood, Paul S. Gregg, Gerry D. Miller, Jeff D. Will, David W. Evans
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Patent number: 7642481Abstract: An apparatus and method for forming a stringer are provided. The stringer generally includes a web having a desired corrugated configuration and first and second flanges welded to opposite edges of the web. The apparatus includes a support structure, a strongback that is supported by the support structure, and a plurality of dies that are adjustable relative to the strongback. The strongback defines a corrugated contour surface corresponding to the desired corrugated configuration of the web. The dies define corresponding forming surfaces and are configured to be advanced toward the strongback to thereby form the web to the desired corrugated configuration between the contour surface of the strongback and the forming surfaces of the dies. Further, the apparatus can receive the flanges of the stringer in a predetermined configuration with the web so that the flanges can be welded to the web while the web is supported by the strongback and dies in the desired corrugated configuration.Type: GrantFiled: August 15, 2006Date of Patent: January 5, 2010Assignee: The Boeing CompanyInventors: Max U. Kismarton, Paul S. Gregg, Jeff D. Will
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Publication number: 20080142489Abstract: A self-adjusting trailing shield for maintaining a volume of inert gas over a portion of a metal workpiece being subjected to a metal processing operation. The shield has segmented side walls, each segment being independently vertically displaceable as the shield is carried in a horizontal plane across a contoured surface of a workpiece. Each segment will be forced upward when it contacts and slides up a rising surface portion of the workpiece. Each segment is coupled to a respective spring that restores each deflected segment to its original, i.e., fully extended, position as the segment slides down a falling surface. The result is a continual reconfiguration of the segmented side walls that reduces the amount of inert gas escaping from the cover space during travel of the shield, as compared to a shield having rigid, not segmented, side walls.Type: ApplicationFiled: December 19, 2006Publication date: June 19, 2008Inventors: Charles S. Willis, Gregory L. Ramsey, Jeff D. Will
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Publication number: 20080105661Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.Type: ApplicationFiled: November 2, 2006Publication date: May 8, 2008Applicant: The Boeing CompanyInventors: Brad L. Kirkwood, Paul S. Gregg, Gerry D. Miller, Jeff D. Will, David W. Evans
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Publication number: 20080040926Abstract: An apparatus and method for forming a stringer are provided. The stringer generally includes a web having a desired corrugated configuration and first and second flanges welded to opposite edges of the web. The apparatus includes a support structure, a strongback that is supported by the support structure, and a plurality of dies that are adjustable relative to the strongback. The strongback defines a corrugated contour surface corresponding to the desired corrugated configuration of the web. The dies define corresponding forming surfaces and are configured to be advanced toward the strongback to thereby form the web to the desired corrugated configuration between the contour surface of the strongback and the forming surfaces of the dies. Further, the apparatus can receive the flanges of the stringer in a predetermined configuration with the web so that the flanges can be welded to the web while the web is supported by the strongback and dies in the desired corrugated configuration.Type: ApplicationFiled: August 15, 2006Publication date: February 21, 2008Inventors: Max U. Kismarton, Paul S. Gregg, Jeff D. Will
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Patent number: 7210611Abstract: A superplastically formed structural assembly is provided, as is an associated preform and method for forming such an assembly. The assembly includes a skin member and a support member that are joined to define a space between the members and between the joints. The assembly can be produced by joining the members in a flat configuration, and then forming the resulting preform to a predetermined shape of the structural assembly. The support member defines at least one aperture in communication with the space between the members. Thus, the skin member can be formed by delivering a pressurized fluid through the support member to the skin member, e.g., to superplastically form the skin member against a die that defines a contour surface corresponding in shape to the predetermined configuration of the assembly. The support member can extend in a substantially direct configuration between opposing portions of the skin member.Type: GrantFiled: October 21, 2004Date of Patent: May 1, 2007Assignee: The Boeing CompanyInventors: Daniel G. Sanders, David W. Foutch, Jeff D. Will, Luis Leon, Gregory L. Ramsey, Garry A. Booker
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Patent number: 5534354Abstract: A method to superplastic form sandwich structures is provided. A series of worksheets are joined together at selected locations through the use of partial penetration welding. The worksheets are subsequently superplastic formed in order to form a sandwich structure. The method allows a different number of worksheets to be used at different points throughout the sandwich structure. This results in a sandwich structure with a different internal reinforcement at different locations in the sandwich structure. In the preferred embodiment, a wing is fabricated from a series of worksheets partial penetration welded together using a laser. The worksheets are superplastic formed to producing a wing with a different internal reinforcement at two or more locations in the wing. The wing includes a pair of double thickness skins that define a major portion of aerodynamically smooth outer surface of the airfoil.Type: GrantFiled: June 7, 1995Date of Patent: July 9, 1996Assignee: The Boeing CompanyInventors: Paul S. Gregg, Matthew G. Kistner, Jeff D. Will
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Patent number: 5451472Abstract: A method to superplastic form sandwich structures is provided. A series of worksheets are joined together at selected locations through the use of partial penetration welding. The worksheets are subsequently superplastic formed in order to form a sandwich structure. The method allows a different number of worksheets to be used at different points throughout the sandwich structure. This results in a sandwich structure with a different internal reinforcement at different locations in the sandwich structure. In the preferred embodiment, a wing is fabricated from a series of worksheets partial penetration welded together using a laser. The worksheets are superplastic formed to producing a wing with a different internal reinforcement at two or more locations in the wing.Type: GrantFiled: February 14, 1994Date of Patent: September 19, 1995Assignee: The Boeing CompanyInventors: Paul S. Gregg, Matthew G. Kistner, Jeff D. Will
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Patent number: 5330092Abstract: A method to superplastic form sandwich structures is provided. A series of worksheets are joined together at selected locations through the use of partial penetration welding. The worksheets are subsequently superplastic formed in order to form a sandwich structure. The method allows a different number of worksheets to be used at different points throughout the sandwich structure. This results in a sandwich structure with a different internal reinforcement at different locations in the sandwich structure. In the preferred embodiment, a wing is fabricated from a series of worksheets partial penetration welded together using a laser. The worksheets are superplastic formed to producing a wing with a different internal reinforcement at two or more locations in the wing.Type: GrantFiled: December 17, 1991Date of Patent: July 19, 1994Assignee: The Boeing CompanyInventors: Paul S. Gregg, Matthew G. Kistner, Jeff D. Will