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公开(公告)号：US20220119092A1
公开(公告)日：2022-04-21
申请号：US17387171
申请日：2021-07-28
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick B. Stickler
Abstract: An apparatus including one or more panels including an outer face sheet comprising a plurality of first composite materials; an inner face sheet comprising a plurality of second composite materials; and a plurality of foam pieces disposed between the outer face sheet and the inner face sheet, wherein the foam pieces reduce warping of the panels.
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公开(公告)号：US20220033061A1
公开(公告)日：2022-02-03
申请号：US17376140
申请日：2021-07-14
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Waeil M. Ashmawi , Sahrudine Apdalhaliem
Abstract: A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.
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公开(公告)号：US20220033060A1
公开(公告)日：2022-02-03
申请号：US17376124
申请日：2021-07-14
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick B. Stickler
Abstract: 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.
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公开(公告)号：US10940936B2
公开(公告)日：2021-03-09
申请号：US15647722
申请日：2017-07-12
Applicant: THE BOEING COMPANY
Inventor： Patrick B. Stickler , Forouzan Behzadpour
IPC: B64C3/18 , B64C1/06 , B64C1/12 , B64C3/26 , B29C70/30 , B29D99/00 , B32B5/26 , B64C3/20 , B64C1/00 , B29L31/30
Abstract: 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.
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公开(公告)号：US10689085B2
公开(公告)日：2020-06-23
申请号：US15913488
申请日：2018-03-06
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Jiangtian Cheng
Abstract: Stringer stiffened composite panels having improved pull-off strength are disclosed. An example stringer includes a first surface, a second surface, an edge, and a chamfer. The second surface is located opposite the first surface and is to be coupled to a composite structure of an aircraft. The edge extends from the second surface toward the first surface. The chamfer extends from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.
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Patent Agency Ranking
公开(公告)号：US20180072399A1
公开(公告)日：2018-03-15
申请号：US15264209
申请日：2016-09-13
Applicant: The Boeing Company
Inventor： Steven P. Walker , Forouzan Behzadpour , Gary D. Oakes , Ian E. Schroeder , Patrick B. Stickler , Jason H. Inouye
Abstract: 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.
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公开(公告)号：US20160052214A1
公开(公告)日：2016-02-25
申请号：US14466954
申请日：2014-08-22
Applicant: The Boeing Company
Inventor： Anthony K. Gilbert , Omid B. Nakhjavani , Shahriar Khosravani , Mohammad Ali Heidari , James F. Ackermann , Mostafa Rassaian , Forouzan Behzadpour
CPC classification number: B29C70/38 , B29C70/30 , B29L2031/3076 , G05B11/011
Abstract: A system and method for creating an optimized composite laminate structure containing a plurality of plies. The system has a processor and a memory, including an application interface. The application interface, when executed by the processor, is configured to operably: receive an input file having one or more of a maximum number of plies, design variables, material properties, and design constraints; determine an initial layup sequence defining parameters of a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle; iteratively adjust the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety, and that achieves optimization of the composite laminate structure; and generate an output file for creating a layup, according to the parameters. The system further has a layup system for creating the optimized composite laminate structure.
Abstract translation: 一种用于产生包含多个层的优化复合层压结构的系统和方法。 该系统具有处理器和存储器，包括应用程序接口。 所述应用程序界面在由所述处理器执行时被配置为可操作地：接收具有最大数量的层数，设计变量，材料属性和设计约束中的一个或多个的输入文件; 确定限定每个层的纤维取向角的参数的初始铺层顺序，以及给定纤维取向角的层的总百分比; 迭代地调整参数，直到获得达到一个或多个预定安全边缘的最佳参数集合，并且实现复合层压结构的优化; 并根据参数生成用于创建叠加的输出文件。 该系统还具有用于产生优化的复合层压结构的铺层系统。
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公开(公告)号：US11623733B2
公开(公告)日：2023-04-11
申请号：US17376140
申请日：2021-07-14
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Waeil M. Ashmawi , Sahrudine Apdalhaliem
Abstract: A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.
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公开(公告)号：US11377851B2
公开(公告)日：2022-07-05
申请号：US16782170
申请日：2020-02-05
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick B. Stickler
Abstract: Provided is a stringer having a first stiffener extending along a path and having a first flange portion and a first web portion, wherein the first stiffener is formed from a composite including a fabric reinforcement; a second stiffener extending along the path and having a second flange portion and a second web portion, the first web portion being opposed and spaced from the second web portion, wherein the second stiffener is formed from a composite including a fabric reinforcement; and an intermediate stiffener extending along the path, the intermediate stiffener being positioned between the first web portion and the second web portion, the intermediate stiffener having a first side and a second side, the first side being connected to the first web portion and the second side being connected to the second web portion, wherein the intermediate stiffener is formed from a composite including unidirectional reinforcement fibers.
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公开(公告)号：US11214349B2
公开(公告)日：2022-01-04
申请号：US16580743
申请日：2019-09-24
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour
Abstract: Stringers and aircraft skin structures and related methods are disclosed. An example apparatus includes a skin structure and a support. The support includes a first surface, a second surface opposite the first surface, and a tapered edge extending from the first surface. The example apparatus includes a first material disposed between a first portion of the support and a first portion of the skin structure to couple the second surface of the support to the skin structure and a second material disposed between a second portion of the support and a second portion of the skin structure. The second material is different than the first material. The second portion of the support includes at least a portion of the tapered edge.
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