公开(公告)号：US10780611B2

公开(公告)日：2020-09-22

申请号：US16010905

申请日：2018-06-18

Applicant: The Boeing Company

Inventor： Kristofer L. Peterson ,  Eileen E. Miller ,  Mark Allen Ulvin ,  Ronald Leroy McGhee ,  David A. Lilienthal

IPC: B29C35/02 ,  B29C70/54 ,  B32B3/08 ,  B32B7/08 ,  B32B7/12 ,  B32B27/08 ,  B29C70/30 ,  B29L31/30

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.

公开(公告)号：US20190381700A1

公开(公告)日：2019-12-19

申请号：US16010905

申请日：2018-06-18

Applicant: The Boeing Company

Inventor： Kristofer L. Peterson ,  Eileen E. Miller ,  Mark Allen Ulvin ,  Ronald Leroy McGhee ,  David A. Lilienthal

IPC: B29C35/02 ,  B32B3/08 ,  B32B7/08 ,  B32B27/08 ,  B29C70/54 ,  B32B7/12

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.

公开(公告)号：US11701796B2

公开(公告)日：2023-07-18

申请号：US17526718

申请日：2021-11-15

Applicant: THE BOEING COMPANY

Inventor： Courtney Michele Fix ,  Robert Wayne Murray ,  Paul Diep ,  Robert E. Lee ,  Richard A. Skilton ,  Ronald Leroy McGhee ,  Zachary Nathaniel Stoddard ,  Patrick B. Stone ,  Phillip Andrew Taylor ,  Nickolas Scott Ellerbeck

IPC: B29C33/48 ,  B64C1/06 ,  B29C33/44 ,  B29C37/00 ,  B29L31/30

CPC classification number: B29C33/485 ,  B29C33/44 ,  B29C37/0003 ,  B64C1/064 ,  B29L2031/3082

Abstract: A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.

公开(公告)号：US20220193958A1

公开(公告)日：2022-06-23

申请号：US17526718

申请日：2021-11-15

Applicant: THE BOEING COMPANY

Inventor： Courtney Michele Fix ,  Robert Wayne Murray ,  Paul Diep ,  Robert E. Lee ,  Richard A. Skilton ,  Ronald Leroy McGhee ,  Zachary Nathaniel Stoddard ,  Patrick B. Stone ,  Phillip Andrew Taylor ,  Nickolas Scott Ellerbeck

IPC: B29C33/48 ,  B64C1/06

Abstract: A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.

公开(公告)号：US11524762B2

公开(公告)日：2022-12-13

申请号：US16798187

申请日：2020-02-21

Applicant: The Boeing Company

Inventor： Zachary Nathaniel Stoddard ,  Ronald Leroy McGhee

IPC: B64C1/06 ,  B64F5/10

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.

公开(公告)号：US20210261230A1

公开(公告)日：2021-08-26

申请号：US16798187

申请日：2020-02-21

Applicant: The Boeing Company

Inventor： Zachary Nathaniel Stoddard ,  Ronald Leroy McGhee

IPC: B64C1/06 ,  B64F5/10

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.