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1. 外观设计

USD941742S1 Aircraft 有权
公开(公告)号：USD941742S1
公开(公告)日：2022-01-25
申请号：US29716765
申请日：2019-12-11
申请人： The Boeing Company
设计人： Gregory M. Schmidt , Kenneth D. Cominsky

2. 发明申请

US20180345591A1 METHOD OF CREATING LARGE COMPLEX COMPOSITE PANELS USING CO-CONSOLIDATION OF THERMOPLASTIC MATERIAL SYSTEMS 审中-公开
公开(公告)号：US20180345591A1
公开(公告)日：2018-12-06
申请号：US15608245
申请日：2017-05-30
申请人： The Boeing Company
发明人： Kenneth D. Cominsky , Trevor Shane McCrea , David Eric Gideon , Bernhard Dopker , Paul Diep , Julie Frances Murphy , Jordan Seth Erickson
IPC分类号： B29C65/00
CPC分类号： B29C43/021 , B29C65/02 , B29C66/0384 , B29C66/1122 , B29C66/1162 , B29C66/12443 , B29C66/12464 , B29C66/1282 , B29C66/12822 , B29C66/12841 , B29C66/12842 , B29C66/12862 , B29C66/43 , B29C66/435 , B29C66/4722 , B29C66/7212 , B29C66/73921 , B29D99/001 , B29K2101/12 , B29K2105/06 , B29K2307/04 , B29L2031/3076
摘要： A method of constructing a large, complex composite panel involves connecting smaller compression molded thermoplastic subpanels, edge to edge using a thermoplastic co-consolidation method. The edges of adjacent subpanels are given complementary surface configurations. The surface configurations are overlapped and heat and pressure are applied to the overlapping surface constructions to co-consolidate the surface constructions in forming a large, composite panel of two or more subpanels.

3. 发明授权

US09227718B2 Lower joints between outboard wing boxes and center wing sections of aircraft wing assemblies 有权
标题翻译：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
申请人： The Boeing Company
发明人： Kenneth D. Cominsky , Jordan Daniel Charles
IPC分类号： B64C1/00 , B64C1/26
CPC分类号： B64C1/26
摘要： 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.
摘要翻译：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。

4. 发明授权

US10994823B2 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
申请人： The Boeing Company
发明人： Kenneth D. Cominsky
IPC分类号： B64C1/06 , B29C70/34 , B21D22/00 , B29L31/30 , B64C1/00
摘要： 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.

5. 发明授权

US09387629B2 Composite hat stiffener, composite hat-stiffened pressure webs, and methods of making the same 有权
标题翻译：复合帽加强筋，复合帽加强筋，及其制造方法
公开(公告)号：US09387629B2
公开(公告)日：2016-07-12
申请号：US14312401
申请日：2014-06-23
申请人： The Boeing Company
发明人： Steven E. Pearson , Matthew M. Whitmer , Rebecca M. Dixon , Jason L. Firko , Douglas G. Marciniak , Kenneth D. Cominsky , Martin G. Andrews
IPC分类号： B21D53/92 , B29C70/46 , B29C70/86 , B29D99/00 , B64C1/06 , B64C1/10 , B29C70/54 , B64C3/26 , B64C1/00
CPC分类号： B29C70/462 , B29C70/545 , B29C70/865 , B29D99/0003 , B64C1/064 , B64C1/10 , B64C3/26 , B64C2001/0072 , Y02T50/43 , Y10T156/1028 , Y10T428/24488 , Y10T428/24628
摘要： 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.
摘要翻译：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，一对半圆形填料面耦合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。

6. 发明申请

US20180015996A1 FRICTION STIR WELDED WINGTIP TORQUE BOX 审中-公开
公开(公告)号：US20180015996A1
公开(公告)日：2018-01-18
申请号：US15209974
申请日：2016-07-14
申请人： The Boeing Company
发明人： Michael P. Shemkunas , Kenneth D. Cominsky , Steven S. Heer , David P. Heck , Benjamin D. Smith , John A. Baumann , Matthew D. Uhlman , Burke L. Reichlinger , Eric E. Thomas , James P. Dobberfuhl
IPC分类号： B64C3/18 , B64C3/26 , C25D11/04 , B23K20/233 , B23K20/12 , B23K103/10 , B23K101/12
CPC分类号： B64C3/18 , B23K20/1265 , B23K20/2336 , B23K2101/12 , B23K2103/10 , B64C3/182 , B64C3/185 , B64C3/20 , B64C3/26 , B64C23/065 , B64F5/10 , C25D11/04 , Y02T50/164
摘要： Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.

7. 发明申请

US20140299257A1 COMPOSITE HAT STIFFENER, COMPOSITE HAT-STIFFENED PRESSURE WEBS, AND METHODS OF MAKING THE SAME 有权
标题翻译：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
申请人： The Boeing Company
发明人： Steven E. Pearson , Matthew M. Whitmer , Rebecca M. Dixon , Jason L. Firko , Douglas G. Marciniak , Kenneth D. Cominsky , Martin G. Andrews
IPC分类号： B29C70/46 , B29C70/54
CPC分类号： B29C70/462 , B29C70/545 , B29C70/865 , B29D99/0003 , B64C1/064 , B64C1/10 , B64C3/26 , B64C2001/0072 , Y02T50/43 , Y10T156/1028 , Y10T428/24488 , Y10T428/24628
摘要： 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.
摘要翻译：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。

8. 发明授权

US11136107B2 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
申请人： The Boeing Company
发明人： Kenneth D. Cominsky , Brent Edward Beneke
IPC分类号： B64C1/26 , B64F5/10
摘要： 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.

9. 发明申请

US20210107619A1 FUSELAGE SECTIONS HAVING TAPERED WING RIB INTERFACES 有权
公开(公告)号：US20210107619A1
公开(公告)日：2021-04-15
申请号：US16597081
申请日：2019-10-09
申请人： The Boeing Company
发明人： Richard R. Rosman , Kenneth D. Cominsky , Branko Lakic
IPC分类号： B64C1/26 , B64C3/18
摘要： Fuselage sections having tapered wing rib interfaces are disclosed. A disclosed example apparatus includes a rib associated with a fuselage section, and a wing interface surface defined by the rib, where the wing interface surface is tapered relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section.

10. 发明授权

US10479474B2 Friction stir welded wingtip torque box 有权
公开(公告)号：US10479474B2
公开(公告)日：2019-11-19
申请号：US15209974
申请日：2016-07-14
申请人： The Boeing Company
发明人： Michael P. Shemkunas , Kenneth D. Cominsky , Steven S. Heer , David P. Heck , Benjamin D. Smith , John A. Baumann , Matthew D. Uhlman , Burke L. Reichlinger , Eric E. Thomas , James P. Dobberfuhl
IPC分类号： B64C3/18 , B23K20/12 , B23K20/233 , B64C3/26 , C25D11/04 , B23K101/12 , B23K103/10
摘要： Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.

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