Ronald Leroy Mcghee

US Patent:

20210261230, Aug 26, 2021

Filed:

Feb 21, 2020

Appl. No.:

16/798187

Inventors:

- Chicago IL, US
Ronald Leroy McGhee - Lynnwood WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 1/06
B64F 5/10

Abstract:

A fuselage structure splice may include a panel having an edge and a strap connected to the first panel along the panel edge. A strap surface not in contact with the panel tapers toward the panel with distance from the panel edge. A stringer is mounted on the panel and extends away from the edge of the panel and has a flange mounted to the panel. A fitting has a stringer base portion and a strap base portion. The stringer base portion is connected to the stringer flange and extends along a first line extending in a plane normal to the panel edge. The strap base portion of the fitting is mounted on the strap surface and extends along a second line in the plane. The second line is transverse to the first line and the strap base portion of the fitting has a constant thickness along the second line.

US Patent:

20210016524, Jan 21, 2021

Filed:

Jul 16, 2019

Appl. No.:

16/513027

Inventors:

- Chicago IL, US
Ronald L. McGhee - Lynnwood WA, US
Devin A. Good - Snohomish WA, US
Wade A. Oswald - Mukilteo WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B29C 70/54
B32B 3/26
B29C 70/30
B32B 27/08

Abstract:

A method for manufacturing a composite structure. The method includes trimming plies of composite material to a near net-shape, thereby yielding a plurality of net-trimmed plies, wherein each net-trimmed ply of the plurality of net-trimmed plies includes an edge. The method further includes assembling a layup that includes the plurality of net-trimmed plies, wherein the assembling of the layup includes staggering the edges of the plurality of net-trimmed plies such that the edges define a staggered edge structure. The method further includes pressing the layup to form the staggered edge structure into a bevel.

US Patent:

20190381700, Dec 19, 2019

Filed:

Jun 18, 2018

Appl. No.:

16/010905

Inventors:

- Chicago IL, US
Eileen E. Miller - Summerville SC, US
Mark Allen Ulvin - Brier WA, US
Ronald Leroy McGhee - Lynnwood WA, US
David A. Lilienthal - Summerville SC, US

International Classification:

B29C 35/02
B32B 3/08
B32B 7/08
B32B 27/08
B29C 70/54
B32B 7/12

Abstract:

A method for fabricating a composite structure is provided. A first number of layers of composite material is laid up to form a first set of stiffeners. A second number of layers of composite material is laid up to form a panel. The first set of stiffeners is associated with a first side of the panel. A pre-cured composite strip is positioned on a second side of the panel, opposite the first side. A third number of layers of composite material is laid up on the second side of the panel to form a second set of stiffeners running perpendicular to the first set of stiffeners. The pre-cured composite lies at an intersection between one of the first set of stiffeners and one of the second set of stiffeners. All the layers of composite material are co-cured to form the composite structure.