-
公开(公告)号：US11643184B2
公开(公告)日：2023-05-09
申请号：US17376119
申请日：2021-07-14
申请人： The Boeing Company
摘要： A wing assembly include at least one fuel tank having a tank outboard end. In addition, the wing assembly includes a stout wing rib located proximate the tank outboard end and extending between a front spar and a rear spar. The wing assembly also includes at least one outboard wing rib located outboard of the stout wing rib and defining an outboard wing bay. The wing assembly also includes an upper skin panel and a lower skin panel each coupled to the front spar, the rear spar, the stout wing rib, and the outboard wing rib. A plurality of bead stiffeners are coupled to the upper skin panel and/or the lower skin panel and are spaced apart from each other within the outboard wing bay.
-
公开(公告)号：US11321501B2
公开(公告)日：2022-05-03
申请号：US16551126
申请日：2019-08-26
申请人： The Boeing Company
摘要： A method, apparatus, and system for managing a composite part. An acceptable level of a warpage is identified for the composite part. The warpage for the composite part is a change in the composite part as manufactured that deviates from design specifications for the composite part. Orientations in a stacking sequence for plies in the composite part are selected that result in the composite part having the acceptable level of the warpage and a desired strength to form selected orientations. The composite part is manufactured using the selected orientations.
-
公开(公告)号：US20220033058A1
公开(公告)日：2022-02-03
申请号：US17376119
申请日：2021-07-14
申请人： The Boeing Company
摘要： A wing assembly include at least one fuel tank having a tank outboard end. In addition, the wing assembly includes a stout wing rib located proximate the tank outboard end and extending between a front spar and a rear spar. The wing assembly also includes at least one outboard wing rib located outboard of the stout wing rib and defining an outboard wing bay. The wing assembly also includes an upper skin panel and a lower skin panel each coupled to the front spar, the rear spar, the stout wing rib, and the outboard wing rib. A plurality of bead stiffeners are coupled to the upper skin panel and/or the lower skin panel and are spaced apart from each other within the outboard wing bay.
-
公开(公告)号：US20220033055A1
公开(公告)日：2022-02-03
申请号：US17376134
申请日：2021-07-14
申请人： The Boeing Company
摘要： A structure has a net-area-tension fastener pattern formed in the skin panel for receiving fasteners defining a net-area-tension joint for coupling a component attach fitting of a component to the skin panel. The net-area-tension fastener pattern includes two or more rows of fastener holes, including a first row and a last row. Each row is oriented generally perpendicular to a primary load direction of a load that the component is capable of exerting on the skin panel. The first row is located upstream of the last row relative to the primary load direction. The fastener holes in the first row and the last row are respectively the smallest and the largest in the net-area-tension fastener pattern. The rows are spaced apart at a spacing ratio of hole spacing to hole diameter. The spacing ratio of the first row is greater than the spacing ratio of the last row.
-
公开(公告)号：US11878793B2
公开(公告)日：2024-01-23
申请号：US17387193
申请日：2021-07-28
申请人： The Boeing Company
IPC分类号： B64C3/00 , B29C70/00 , B29D99/00 , B64C3/20 , B64C3/26 , B29C70/08 , B29C70/38 , B64C3/18 , B29L31/30
CPC分类号： B64C3/20 , B29C70/086 , B29C70/386 , B29D99/0014 , B64C3/182 , B64C3/26 , B29L2031/3085
摘要： A panel including an outer face sheet; an inner face sheet; a foam disposed between the outer face sheet and the inner face sheet; and a core structure (e.g., a stringer comprising a hat structure) between the foam and the inner face sheet; and between the foam and the outer face sheet. The core structure is protected from impact damage and increases flexural stiffness of the panel on an aircraft wing.
-
公开(公告)号：US11613341B2
公开(公告)日：2023-03-28
申请号：US17376124
申请日：2021-07-14
申请人： The Boeing Company
摘要： A wing assembly includes a center wing structure and a pair of outer wing structures. The center wing structure includes a center wing front spar, a center wing rear spar, and an engine mounting location on each side of a wing centerline. Each outer wing structure includes an outer wing front and rear spar configured to be coupled respectively to the center wing front and rear spar to define a wing joint coupling the outer wing structure to the center wing structure. The center wing structure is configured such that the spar terminal ends of the center wing front and rear spars at each wing joint are located no further inboard than an engine centerline associated with the engine mounting location, and no further outboard of the engine centerline than ten percent of a distance between the engine centerline and the wing centerline.
-
公开(公告)号：US11584502B2
公开(公告)日：2023-02-21
申请号：US17443026
申请日：2021-07-20
申请人： The Boeing Company
摘要： A composite hat stringer for stiffening a panel includes a plurality of composite fabric plies arranged to form a cap, a pair of flanges and a pair of webs respectively connecting the cap with the pair of flanges. The cap includes at least one 0° composite tape ply interleafed in the composite fabric plies within the cap.
-
公开(公告)号：US20210339843A1
公开(公告)日：2021-11-04
申请号：US16866193
申请日：2020-05-04
申请人： The Boeing Company
摘要： Described herein are stringer assemblies, such as blade stringers, and methods of forming thereof. A stringer assembly comprises a first fabric composite stiffener, a second fabric composite stiffener, and an intermediate tape composite stiffener, disposed between and connected to each of the first and second stiffeners. Using three separate components allows forming sharp bends, eliminating voids and gap fillers, and adding new features, such as edge reinforcements. Each of the first and second fabric composite stiffeners comprises a web portion, a flange portion, and a curved portion, positioned between the web and flange portions. The web portions surround and are attached to the intermediate tape composite stiffener and, in some examples, include tapered-out edges for additional rigidity. The flange portions are attached to the composite base. The curved portions conform to the flared-out edges of the intermediate tape composite stiffener, which extends and connects to the composite base.
-
公开(公告)号：US10974478B2
公开(公告)日：2021-04-13
申请号：US16296687
申请日：2019-03-08
申请人： The Boeing Company
发明人： Forouzan Behzadpour
摘要： An interleaved layer construction of a composite panel and a composite plank constructed of three sub-planks that are adhered together and secured to the panel stiffen and strengthen the panel.
-
公开(公告)号：US20190016436A1
公开(公告)日：2019-01-17
申请号：US15647722
申请日：2017-07-12
申请人： THE BOEING COMPANY
摘要： A composite assembly includes a composite skin which includes a plurality of composite plies and a composite stringer secured to the composite skin. A first composite plank ply is positioned between a first pair of composite plies of the plurality of composite plies of the composite skin; the first composite plank ply has a width dimension less than a width dimension of the plurality of composite plies of the composite skin; and the first composite plank ply extends along a length of the composite stringer. At least a portion of the composite stringer is positioned in overlying relationship with the first composite plank ply.
-
-
-
-
-
-
-
-
-
搜索结果
36 条记录 (耗时 0.018 秒)
