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    Joint member for a composite wing structure
    1.
    发明授权
    Joint member for a composite wing structure 有权

    公开(公告)号：US10513325B2

    公开(公告)日：2019-12-24

    申请号：US15424338

    申请日：2017-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： James E. Kooiman ,  George R. Decker ,  Charles D. Hogue

    IPC: B64C3/18 ,  B64C3/26 ,  B64F5/10 ,  B64C29/00

    Abstract: In one aspect, there is a joint member for a composite having a laminate layer including a support member having a first side and a second side; a first flange extending laterally from the first side and having an attachment surface for attachment to a structure; and a second flange extending laterally from the second side and having an attachment surface configured for attachment to the laminate layer. The joint member is configured to provide a load path from the first flange to the second flange. In an embodiment, a joint system for a composite system includes a joint member attached to a first skin and a second skin. In still another embodiment, a joint system for a rib assembly includes a joint member attached to a rib web and rib post.

    JOINT MEMBER FOR A COMPOSITE WING STRUCTURE
    6.
    发明申请
    JOINT MEMBER FOR A COMPOSITE WING STRUCTURE 审中-公开

    公开(公告)号：US20170225770A1

    公开(公告)日：2017-08-10

    申请号：US15424338

    申请日：2017-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： James E. Kooiman ,  George R. Decker ,  Charles D. Hogue

    IPC: B64C3/26 ,  B64C3/18 ,  B64F5/10

    Abstract: In one aspect, there is a joint member for a composite having a laminate layer including a support member having a first side and a second side; a first flange extending laterally from the first side and having an attachment surface for attachment to a structure; and a second flange extending laterally from the second side and having an attachment surface configured for attachment to the laminate layer. The joint member is configured to provide a load path from the first flange to the second flange. In an embodiment, a joint system for a composite system includes a joint member attached to a first skin and a second skin. In still another embodiment, a joint system for a rib assembly includes a joint member attached to a rib web and rib post.

    ENGAGEMENT MEMBER FOR SPLICING A SPAR ASSEMBLY
    7.
    发明申请
    ENGAGEMENT MEMBER FOR SPLICING A SPAR ASSEMBLY 审中-公开

    公开(公告)号：US20170225767A1

    公开(公告)日：2017-08-10

    申请号：US15424402

    申请日：2017-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： James E. King ,  James E. Kooiman ,  Charles D. Hogue

    IPC: B64C3/18 ,  F16B11/00 ,  F16B5/01

    Abstract: In one aspect, there is an engagement member for splicing a spar assembly in an aircraft wing including a joining portion having a first attachment for connecting to a first spar and a second attachment surface for connecting to a second spar; and a rib post extending from the joining portion and disposed between the first attachment surface and the second attachment surface. In an embodiment, the rib post is integral to the joining portion and is configured to couple with a rib web.

    Composite rib assembly
    9.
    发明授权
    Composite rib assembly 有权

    公开(公告)号：US10513324B2

    公开(公告)日：2019-12-24

    申请号：US15424095

    申请日：2017-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David G. Carlson ,  John R. McCullough ,  Paul K. Oldroyd ,  Carl A. May ,  James E. Kooiman

    IPC: B64C3/18 ,  B64C3/26 ,  B64F5/10 ,  B64C29/00

    Abstract: In one aspect, there is a rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.

    COMPOSITE RIB ASSEMBLY
    10.
    发明申请
    COMPOSITE RIB ASSEMBLY 审中-公开

    公开(公告)号：US20170225766A1

    公开(公告)日：2017-08-10

    申请号：US15424095

    申请日：2017-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David G. Carlson ,  John R. McCullough ,  Paul K. Oldroyd ,  Carl A. May ,  James E. Kooiman

    IPC: B64C3/18 ,  B64C3/26

    Abstract: In one aspect, there is a rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.

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