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    Methods and systems for repairing composite structures
    1.
    发明授权
    Methods and systems for repairing composite structures 有权

    公开(公告)号：US11040496B2

    公开(公告)日：2021-06-22

    申请号：US15847294

    申请日：2017-12-19

    申请人： THE BOEING COMPANY

    发明人： Steven Donald Blanchard ,  Gary D. Oakes ,  Arne K. Lewis

    IPC分类号： B29C65/00 ,  B29C70/44 ,  B32B37/10 ,  B29D99/00 ,  B29C73/10 ,  B29C73/30 ,  B29L31/30 ,  B29C65/18

    摘要： A method of bonding composite structures includes positioning a second structure at a bonding site on a first structure and coupling a first vacuum bag to the first structure such that the first vacuum bag covers the bonding site. The method also includes applying a vacuum to the first vacuum bag to induce a first mechanical force to the second structure via the first vacuum bag. A second vacuum bag is coupled to the first structure such that second vacuum bag covers the second structure and at least a portion of the first vacuum bag. The method further includes applying a vacuum to the second vacuum bag to induce a second mechanical force to the second structure via the second vacuum bag.

    AIRCRAFT WINGS AND AIRCRAFT INCLUDING SUCH AIRCRAFT WINGS
    3.
    发明申请
    AIRCRAFT WINGS AND AIRCRAFT INCLUDING SUCH AIRCRAFT WINGS 审中-公开

    公开(公告)号：US20180072399A1

    公开(公告)日：2018-03-15

    申请号：US15264209

    申请日：2016-09-13

    申请人： The Boeing Company

    发明人： Steven P. Walker ,  Forouzan Behzadpour ,  Gary D. Oakes ,  Ian E. Schroeder ,  Patrick B. Stickler ,  Jason H. Inouye

    IPC分类号： B64C3/18 ,  B64C3/26

    摘要： Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

    Aircraft wings and aircraft including such aircraft wings
    4.
    发明授权
    Aircraft wings and aircraft including such aircraft wings 有权

    公开(公告)号：US10696373B2

    公开(公告)日：2020-06-30

    申请号：US15264209

    申请日：2016-09-13

    申请人： The Boeing Company

    发明人： Steven P. Walker ,  Forouzan Behzadpour ,  Gary D. Oakes ,  Ian E. Schroeder ,  Patrick B. Stickler ,  Jason H. Inouye

    IPC分类号： B64C3/18 ,  B64C1/26 ,  B64C3/26 ,  B64C1/00 ,  B64C1/06

    摘要： Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

    METHOD OF REPAIRING DAMAGE TO FUSELAGE BARREL AND ASSOCIATED APPARATUS AND SYSTEM
    5.
    发明申请
    METHOD OF REPAIRING DAMAGE TO FUSELAGE BARREL AND ASSOCIATED APPARATUS AND SYSTEM 审中-公开

    公开(公告)号：US20190248463A1

    公开(公告)日：2019-08-15

    申请号：US16393716

    申请日：2019-04-24

    申请人： The Boeing Company

    发明人： Remmelt Andrew Staal ,  Narbeh Nersessian ,  Gary D. Oakes

    IPC分类号： B64C1/06 ,  B64F5/40

    CPC分类号： B64C1/06 ,  B64C1/068 ,  B64C1/069 ,  B64C2001/0072 ,  B64F5/40

    摘要： Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.

    SKIN PANEL OF COMPOSITE MATERIAL HAVING AN INTERNAL GRID
    6.
    发明申请
    SKIN PANEL OF COMPOSITE MATERIAL HAVING AN INTERNAL GRID 审中-公开

    公开(公告)号：US20180281923A1

    公开(公告)日：2018-10-04

    申请号：US15471422

    申请日：2017-03-28

    申请人： The Boeing Company

    发明人： Steven P. Walker ,  Gregory M. Santini ,  Gary D. Oakes ,  Patrick B. Stickler

    IPC分类号： B64C3/26 ,  B64C1/12

    摘要： A skin panel configured for attachment to an aircraft structure is constructed of a composite material and has a continuous, smooth outer surface; a continuous, smooth inner surface that is configured for attachment to an aircraft structure; a peripheral edge that extends entirely around the skin panel and has a continuous, smooth surface and a plurality of cavities inside the material of the skin panel. The cavities reduce the weight of the skin panel without significantly detracting from the compression strength and tensile strength of the skin panel.

    Method of repairing damage to fuselage barrel and associated apparatus and system
    8.
    发明授权
    Method of repairing damage to fuselage barrel and associated apparatus and system 有权

    公开(公告)号：US11104412B2

    公开(公告)日：2021-08-31

    申请号：US16393716

    申请日：2019-04-24

    申请人： The Boeing Company

    发明人： Remmelt Andrew Staal ,  Narbeh Nersessian ,  Gary D. Oakes

    IPC分类号： B64C1/06 ,  B64F5/40 ,  B64C1/00

    摘要： Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.

    Method of repairing damage to fuselage barrel and associated apparatus and system
    10.
    发明授权
    Method of repairing damage to fuselage barrel and associated apparatus and system 有权

    公开(公告)号：US10308342B2

    公开(公告)日：2019-06-04

    申请号：US15258919

    申请日：2016-09-07

    申请人： The Boeing Company

    发明人： Remmelt Andrew Staal ,  Narbeh Nersessian ,  Gary D. Oakes

    IPC分类号： B64C1/06 ,  B64F5/40 ,  B64C1/00

    摘要： Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.