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    Lower joints between outboard wing boxes and center wing sections of aircraft wing assemblies
    3.
    发明授权
    Lower joints between outboard wing boxes and center wing sections of aircraft wing assemblies 有权
    飞机机翼组件外侧翼箱与中心翼段之间的下关节

    公开(公告)号：US09227718B2

    公开(公告)日：2016-01-05

    申请号：US13913099

    申请日：2013-06-07

    Applicant: The Boeing Company

    Inventor： Kenneth D. Cominsky ,  Jordan Daniel Charles

    IPC: B64C1/00 ,  B64C1/26

    CPC classification number: B64C1/26

    Abstract: Lower joints of aircraft wing assemblies are disclosed. In some embodiments, a lower joint includes an outboard lower wing panel, a center lower wing panel, a rib, and a lower joint assembly that includes two outboard flanges operatively coupled to the outboard lower wing panel, an inboard flange operatively coupled to the center lower wing panel, and an upper flange operatively coupled to the rib. In some embodiments, a lower joint assembly includes one or more splice plates, an upper T-fitting, and one or more intermediate plates. In some embodiments, the outboard lower wing panel, the center lower wing panel, and the lower joint assembly are constructed substantially of different materials.

    Abstract translation: 公开了飞机机翼组件的下关节。 在一些实施例中，下接头包括外侧下翼板，中心下翼板，肋和下接头组件，其包括可操作地联接到外侧下翼板的两个外侧凸缘，可操作地联接到中心的内侧凸缘 下翼板和可操作地联接到肋的上凸缘。 在一些实施例中，下接头组件包括一个或多个接合板，上T形接头和一个或多个中间板。 在一些实施例中，外侧下翼板，中心下翼板和下接头组件基本上由不同的材料构成。

    COMPOSITE HAT STIFFENER, COMPOSITE HAT-STIFFENED PRESSURE WEBS, AND METHODS OF MAKING THE SAME
    5.
    发明申请
    COMPOSITE HAT STIFFENER, COMPOSITE HAT-STIFFENED PRESSURE WEBS, AND METHODS OF MAKING THE SAME 有权
    复合帽加固剂，复合高强度压力织物及其制造方法

    公开(公告)号：US20140299257A1

    公开(公告)日：2014-10-09

    申请号：US14312401

    申请日：2014-06-23

    Applicant: The Boeing Company

    Inventor： Steven E. Pearson ,  Matthew M. Whitmer ,  Rebecca M. Dixon ,  Jason L. Firko ,  Douglas G. Marciniak ,  Kenneth D. Cominsky ,  Martin G. Andrews

    IPC: B29C70/46 ,  B29C70/54

    CPC classification number: B29C70/462 ,  B29C70/545 ,  B29C70/865 ,  B29D99/0003 ,  B64C1/064 ,  B64C1/10 ,  B64C3/26 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T156/1028 ,  Y10T428/24488 ,  Y10T428/24628

    Abstract: There is provided a method of making a composite hat stiffener. The method has the steps of curing a composite hat stiffener in a hat tool to form a pre-cured composite hat stiffener. The pre-cured composite hat stiffener has a composite hat section, a plurality of composite stiffening plies with a body ply, a wrap ply, and a base ply, all coupled to the composite hat section, wherein the body ply is coupled to a first side of the composite hat section, the wrap ply is coupled to the body ply, and the base ply is coupled to the body ply and the wrap ply, a pair of radius filler noodles coupled to the composite hat section and disposed between the plurality of composite stiffening plies, and an outer ply coupled to the composite hat section. The method further includes bonding the pre-cured composite hat stiffener to a structure surface.

    Abstract translation: 提供了制作复合帽加强件的方法。 该方法具有在帽子工具中固化复合帽加强件以形成预固化的复合帽加强件的步骤。 预固化的复合帽加强件具有复合帽部分，多个具有主体层的复合加强层，包层和底层，全部联接到复合帽部分，其中主体层结合到第一 复合帽部分的一侧，包裹层联接到主体帘布层，并且基底层联接到主体帘布层和包裹层，一对半圆形填料面连接到复合帽部分并且设置在多个 复合加强层和耦合到复合帽部分的外层。 该方法还包括将预固化的复合帽加强件结合到结构表面。

    Serrated fitting
    6.
    发明授权
    Serrated fitting 有权

    公开(公告)号：US12286998B1

    公开(公告)日：2025-04-29

    申请号：US18482451

    申请日：2023-10-06

    Applicant: The Boeing Company

    Inventor： Kenneth D. Cominsky

    IPC: F16B5/02 ,  B64C1/18 ,  B64D9/00 ,  B64F5/10

    Abstract: A serrated fitting and method for installing fixed length roller tray segments spanning an aircraft fuselage integration zone. The serrated fitting includes a first surface for attachment to a fixed length roller tray segment. The serrated fitting also includes a serrated surface for engagement with a serrated plate attached to a floor beam of an aircraft. A fastener connects the serrated surface to the serrated plate and the floor beam through a pre-drilled hole in the floor beam. The pre-drilled hole is larger than the diameter of the fastener to accommodate accumulated tolerance between joined fuselage sections at a fuselage integration zone.

    Serrated Fitting
    7.
    发明申请
    Serrated Fitting 有权

    公开(公告)号：US20250116284A1

    公开(公告)日：2025-04-10

    申请号：US18482451

    申请日：2023-10-06

    Applicant: The Boeing Company

    Inventor： Kenneth D. Cominsky

    IPC: F16B5/02 ,  B64C1/18 ,  B64D9/00 ,  B64F5/10

    Abstract: A serrated fitting and method for installing fixed length roller tray segments spanning an aircraft fuselage integration zone. The serrated fitting includes a first surface for attachment to a fixed length roller tray segment. The serrated fitting also includes a serrated surface for engagement with a serrated plate attached to a floor beam of an aircraft. A fastener connects the serrated surface to the serrated plate and the floor beam through a pre-drilled hole in the floor beam. The pre-drilled hole is larger than the diameter of the fastener to accommodate accumulated tolerance between joined fuselage sections at a fuselage integration zone.

    Beaded panels and method of forming beaded panels
    8.
    发明授权
    Beaded panels and method of forming beaded panels 有权

    公开(公告)号：US10994823B2

    公开(公告)日：2021-05-04

    申请号：US16158028

    申请日：2018-10-11

    Applicant: The Boeing Company

    Inventor： Kenneth D. Cominsky

    IPC: B64C1/06 ,  B29C70/34 ,  B21D22/00 ,  B29L31/30 ,  B64C1/00

    Abstract: Beaded panels and method of forming beaded panels. A beaded panel as described herein includes a base structure comprising a sheet of material, and beads that comprise a protrusion on a first side of the base structure, and a concavity on an opposing second side of the base structure. A geometry of the beads comprises a center section having a conic shape about a longitudinal axis, flared sections symmetric about the center section along the longitudinal axis, and a transition section that curves outward from a base of the center section and the flared sections to blend with a flat surface on the first side of the base structure.

    Method and apparatus for attaching a fuselage frame to a wing box
    10.
    发明授权
    Method and apparatus for attaching a fuselage frame to a wing box 有权

    公开(公告)号：US11136107B2

    公开(公告)日：2021-10-05

    申请号：US16152788

    申请日：2018-10-05

    Applicant: The Boeing Company

    Inventor： Kenneth D. Cominsky ,  Brent Edward Beneke

    IPC: B64C1/26 ,  B64F5/10

    Abstract: An aircraft includes an aircraft body including a longitudinal axis and a wing box extending through the aircraft body. The aircraft also includes an attachment assembly coupled to the aircraft body and to the wing box. The attachment assembly includes a first attachment member coupled to the aircraft body and a second attachment member coupled to the wing box. The second attachment member is configured to couple to the first attachment member. The attachment assembly also includes a plurality of fasteners extending through the first attachment member and the second attachment member such that the plurality of fasteners are loaded in shear during a wing loading condition.

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