Patents by Inventor Barry P. Van West
Barry P. Van West 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).
-
Patent number: 9694895Abstract: A method and apparatus for manufacturing a composite stringer. A composite material and foam are laid up onto a tool in the form of a stringer. The foam has a plurality of structural members within the foam. The plurality of structural members has a number of orientations to resist a number of loads. The composite material, the foam in the form of the stringer, and the plurality of structural members are cured to form the composite stringer.Type: GrantFiled: June 18, 2013Date of Patent: July 4, 2017Assignee: THE BOEING COMPANYInventors: Simon D. Senibi, Barry P. Van West, Juan Carlos Guzman, Douglas A. McCarville, Daniel M. Rotter
-
Publication number: 20130280491Abstract: A method and apparatus for manufacturing a composite stringer. A composite material and foam are laid up onto a tool in the form of a stringer. The foam has a plurality of structural members within the foam. The plurality of structural members has a number of orientations to resist a number of loads. The composite material, the foam in the form of the stringer, and the plurality of structural members are cured to form the composite stringer.Type: ApplicationFiled: June 18, 2013Publication date: October 24, 2013Inventors: Simon D. Senibi, Barry P. Van West, Juan Carlos Guzman, Douglas A. McCarville, Daniel M. Rotter
-
Patent number: 8540921Abstract: A method and apparatus for manufacturing a composite stringer. A composite material and foam are laid up onto a tool in the form of a stringer. The foam has a plurality of structural members within the foam. The plurality of structural members has a number of orientations to resist a number of loads. The composite material, the foam in the form of the stringer, and the plurality of structural members are cured to form the composite stringer.Type: GrantFiled: November 25, 2008Date of Patent: September 24, 2013Assignee: The Boeing CompanyInventors: Simon D. Senibi, Barry P. Van West, Juan Carlos Guzman, Douglas A. McCarville, Daniel M. Rotter
-
Patent number: 8435375Abstract: A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. A skin is applied to a smooth, hard base tool. Ribs comprised of carbon-fiber tows are formed on the skin, and shallow cavities are formed between the ribs and the skin. An expansion block is placed in each of the cavities, and is held in place by an elastomeric contact adhesive having adhesive properties that are substantially diminished when the adhesive is heated to an elevated curing temperature. The assembly is then autoclave cured. After cooling, the formed structure is separated from the base tool and the expansion blocks are removed from the cavities. A grid-stiffened sandwich structure is formed by applying an outer skin over the ribs and expansion blocks, before curing the assembly. After cooling, the outer skin is removed to allow extraction of the blocks, and subsequently bonded to the ribs.Type: GrantFiled: July 26, 2012Date of Patent: May 7, 2013Assignee: The United States as represented by the Secretary of the AirforceInventors: Peter M. Wegner, Jeffrey M. Ganley, Brice A. Johnson, Barry P. Van West
-
Patent number: 8236124Abstract: A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. A skin is applied to a smooth, hard base tool. Ribs comprised of carbon-fiber tows are formed on the skin, and shallow cavities are formed between the ribs and the skin. An expansion block is placed in each of the cavities, and is held in place by an elastomeric contact adhesive having adhesive properties that are substantially diminished when the adhesive is heated to an elevated curing temperature. The assembly is then autoclave cured. After cooling, the formed structure is separated from the base tool and the expansion blocks are removed from the cavities. A grid-stiffened sandwich structure is formed by applying an outer skin over the ribs and expansion blocks, before curing the assembly. After cooling, the outer skin is removed to allow extraction of the blocks, and subsequently bonded to the ribs.Type: GrantFiled: December 14, 2010Date of Patent: August 7, 2012Assignee: The United States of America as represented by the Secretary of the Air ForceInventors: Peter M. Wegner, Jeffrey M. Ganley, Brice A. Johnson, Barry P. Van West
-
Patent number: 8142181Abstract: A method for forming composite materials is presented, including providing a composite charge wider than a first surface of a mandrel, and positioning the composite charge across the first surface of the mandrel. The portion of the composite charge overhanging the first surface of the mandrel is supported and urged against the mandrel while supporting the unbent portion of the composite charge substantially parallel to the first surface of the mandrel. The invention also provides a system, using a compression mold of forming bladders and heater plates, to form a composite charge over a mandrel, while supporting the unbent portions of the composite charge during forming substantially parallel to the upper surface of the mandrel. The present invention minimizes the shear zone where plies in the composite laminate charge slide past one another during the forming process reducing or eliminating out-of-plane fiber buckling.Type: GrantFiled: September 16, 2004Date of Patent: March 27, 2012Assignee: The Boeing CompanyInventors: Kurtis S. Willden, Barry P. Van West, Christopher G. Harris
-
Patent number: 7879276Abstract: A method and apparatus for a composite stringer. A method is used for manufacturing a hollow composite stringer. Foam is formed with a mandrel installed into the foam. A composite material and the foam is laid up onto a tool in a form of a stringer. The composite material and the foam in the form of the stringer is cured to form a cured stringer. The mandrel from the foam is removed to form the hollow composite stringer.Type: GrantFiled: November 8, 2007Date of Patent: February 1, 2011Assignee: The Boeing CompanyInventors: Juan C. Guzman, Douglas A. McCarville, Daniel M. Rotter, Barry P. Van West
-
Patent number: 7871487Abstract: A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. Ribs are formed on a smooth hard base tool. Expansion blocks are placed in the shallow cavities formed by the ribs and the base tool, and held in place by one of several means while a skin is placed over the ribs, expansion blocks, and base tool. The assembly is then placed in a vacuum bag and autoclave cured. After cooling, the formed structure is separated from the base tool and the expansion blocks are removed from the cavities. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.Type: GrantFiled: December 10, 2008Date of Patent: January 18, 2011Assignee: The United States of America as represented by the Secretary of the Air ForceInventors: Peter M. Wegner, Jeffrey M. Ganley, Brice A. Johnson, Barry P. Van West
-
Publication number: 20100129589Abstract: A method and apparatus for manufacturing a composite stringer. A composite material and foam are laid up onto a tool in the form of a stringer. The foam has a plurality of structural members within the foam. The plurality of structural members has a number of orientations to resist a number of loads. The composite material, the foam in the form of the stringer, and the plurality of structural members are cured to form the composite stringer.Type: ApplicationFiled: November 25, 2008Publication date: May 27, 2010Inventors: Simon D. Senibi, Barry P. Van West, Juan Carlos Guzman, Douglas A. McCarville, Daniel M. Rotter
-
Patent number: 7479201Abstract: A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. Ribs are formed on a smooth hard base tool. Expansion blocks are placed in the shallow cavities formed by the ribs and the base tool, and held in place by a synthetic elastomer-based adhesive while a skin is placed over the ribs, expansion blocks, and base tool. The assembly is then placed in a vacuum bag and autoclave cured. After cooling, the expansion blocks are removed and the formed structure is removed from the hard base tool. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.Type: GrantFiled: September 27, 2005Date of Patent: January 20, 2009Assignee: The United States of America as represented by the Secretary of the Air ForceInventors: Peter M. Wegner, Jeffrey M. Ganley, Brice A. Johnson, Barry P. Van West
-
Patent number: 6814916Abstract: A method for forming composite materials is presented, including providing a composite charge wider than a first surface of a mandrel, and positioning the composite charge across the first surface of the mandrel. The portion of the composite charge overhanging the first surface of the mandrel is supported and urged against the mandrel while supporting the unbent portion of the composite charge substantially parallel to the first surface of the mandrel. The invention also provides a system, using a compression mold of forming bladders and heater plates, to form a composite charge over a mandrel, while supporting the unbent portions of the composite charge during forming substantially parallel to the upper surface of the mandrel. The present invention minimizes the shear zone where plies in the composite laminate charge slide past one another during the forming process reducing or eliminating out-of-plane fiber buckling.Type: GrantFiled: August 30, 2002Date of Patent: November 9, 2004Assignee: The Boeing CompanyInventors: Kurtis S. Willden, Christopher G. Harris, Barry P. Van West
-
Patent number: 6709538Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.Type: GrantFiled: May 21, 2002Date of Patent: March 23, 2004Assignee: The Boeing CompanyInventors: Panagiotis E. George, Kirk B. Kajita, Barry P. Van West
-
Publication number: 20040043196Abstract: A method for forming composite materials is presented, including providing a composite charge wider than a first surface of a mandrel, and positioning the composite charge across the first surface of the mandrel. The portion of the composite charge overhanging the first surface of the mandrel is supported and urged against the mandrel while supporting the unbent portion of the composite charge substantially parallel to the first surface of the mandrel. The invention also provides a system, using a compression mold of forming bladders and heater plates, to form a composite charge over a mandrel, while supporting the unbent portions of the composite charge during forming substantially parallel to the upper surface of the mandrel. The present invention minimizes the shear zone where plies in the composite laminate charge slide past one another during the forming process reducing or eliminating out-of-plane fiber buckling.Type: ApplicationFiled: August 30, 2002Publication date: March 4, 2004Inventors: Kurtis S. Willden, Christopher G. Harris, Barry P. Van West
-
Patent number: 6689448Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.Type: GrantFiled: May 21, 2002Date of Patent: February 10, 2004Assignee: The Boeing CompanyInventors: Panagiotis E. George, Kirk B. Kajita, Barry P. Van West
-
Patent number: 6562436Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.Type: GrantFiled: February 23, 2001Date of Patent: May 13, 2003Assignee: The Boeing CompanyInventors: Panagiotis E. George, Kirk B. Kajita, Barry P. Van West
-
Publication number: 20030044570Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.Type: ApplicationFiled: May 21, 2002Publication date: March 6, 2003Inventors: Panagiotis E. George, Kirk B. Kajita, Barry P. Van West
-
Publication number: 20030024630Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.Type: ApplicationFiled: May 21, 2002Publication date: February 6, 2003Applicant: The Boeing CompanyInventors: Panagiotis E. George, Kirk B. Kajita, Barry P. Van West
-
Publication number: 20020031641Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.Type: ApplicationFiled: February 23, 2001Publication date: March 14, 2002Applicant: The Boeing CompanyInventors: Panagiotis E. George, Kirk B. Kajita, Barry P. Van West