Patents by Inventor Samuel E. Cregger
Samuel E. Cregger 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: 10988229Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer may also include a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer may also include a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.Type: GrantFiled: April 23, 2020Date of Patent: April 27, 2021Assignee: The Boeing CompanyInventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
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Publication number: 20200247523Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer may also include a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer may also include a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.Type: ApplicationFiled: April 23, 2020Publication date: August 6, 2020Inventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
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Patent number: 10669005Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.Type: GrantFiled: February 27, 2018Date of Patent: June 2, 2020Assignee: The Boeing CompanyInventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
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Publication number: 20190263496Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.Type: ApplicationFiled: February 27, 2018Publication date: August 29, 2019Inventors: Jiangtian Cheng, Ian E. Schroeder, Gary D. Swanson, Kanna M. Pham, Samuel E. Cregger, Scott M. Spencer
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Patent number: 6114050Abstract: The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.Type: GrantFiled: December 29, 1998Date of Patent: September 5, 2000Assignee: The Boeing CompanyInventors: Willard N. Westre, Heather C. Allen-Lilly, Donald J. Ayers, Samuel E. Cregger, David W. Evans, Donald L. Grande, Daniel J. Hoffman, Mark E. Rogalski, Robert J. Rothschilds
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Patent number: 5866272Abstract: The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.Type: GrantFiled: January 11, 1996Date of Patent: February 2, 1999Assignee: The Boeing CompanyInventors: Willard N. Westre, Heather C. Allen-Lilly, Donald J. Ayers, Samuel E. Cregger, David W. Evans, Donald L. Grande, Daniel J. Hoffman, Mark E. Rogalski, Robert J. Rothschilds