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公开(公告)号：US09856008B2
公开(公告)日：2018-01-02
申请号：US14281456
申请日：2014-05-19
Applicant: The Boeing Company
Inventor： Jiangtian Cheng , Derek Paul Vetter , Patrick Alan Woodard , Forouzan Behzadpour
CPC classification number: B64C1/06 , B29C37/0082 , B29C70/342 , B29C70/865 , B29D99/0003 , B29D99/0014 , B29K2705/00 , B29L2031/3076 , Y02T50/43
Abstract: A composite structure is provided. The composite structure includes a first stiffener, a second stiffener, and an intermediate structure positioned between the first and second stiffeners such that the first stiffener is coupled to a first side of the intermediate structure, and such that the second stiffener is coupled to a second opposing side of the intermediate structure. A first radius gap is defined at least partially between the first stiffener and the intermediate structure, and a second radius gap is defined at least partially between the second stiffener and the intermediate structure.
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公开(公告)号：US20220111948A1
公开(公告)日：2022-04-14
申请号：US17387193
申请日：2021-07-28
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick B. Stickler
Abstract: 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.
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公开(公告)号：US20220033049A1
公开(公告)日：2022-02-03
申请号：US17443026
申请日：2021-07-20
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick Bickford Stickler
Abstract: 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.
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公开(公告)号：US20210238851A1
公开(公告)日：2021-08-05
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：US20210086886A1
公开(公告)日：2021-03-25
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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Patent Agency Ranking
公开(公告)号：US20200086970A1
公开(公告)日：2020-03-19
申请号：US16134570
申请日：2018-09-18
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick B. Stickler
Abstract: An aircraft wing construction of composite materials includes a wing spar having a web constructed of only pre-preg fabric and having first and second spar caps projecting at an angle from opposite edges of the web with the first and second spar caps being constructed of interleaved and alternating portions of the pre-preg fabric of the web and unidirectional pre-preg tapes.
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公开(公告)号：US09770873B2
公开(公告)日：2017-09-26
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.
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公开(公告)号：US20160144943A1
公开(公告)日：2016-05-26
申请号：US14281456
申请日：2014-05-19
Applicant: The Boeing Company
Inventor： Jiangtian Cheng , Derek Paul Vetter , Patrick Alan Woodard , Forouzan Behzadpour
IPC: B64C1/06
CPC classification number: B64C1/06 , B29C37/0082 , B29C70/342 , B29C70/865 , B29D99/0003 , B29D99/0014 , B29K2705/00 , B29L2031/3076 , Y02T50/43
Abstract: A composite structure is provided. The composite structure includes a first stiffener, a second stiffener, and an intermediate structure positioned between the first and second stiffeners such that the first stiffener is coupled to a first side of the intermediate structure, and such that the second stiffener is coupled to a second opposing side of the intermediate structure. A first radius gap is defined at least partially between the first stiffener and the intermediate structure, and a second radius gap is defined at least partially between the second stiffener and the intermediate structure.
Abstract translation: 提供复合结构。 复合结构包括第一加强件，第二加强件和定位在第一和第二加强件之间的中间结构，使得第一加强件联接到中间结构的第一侧，并且使得第二加强件联接到第二加强件 中间结构的相对侧。 第一半径间隙至少部分地限定在第一加强件和中间结构之间，并且第二半径间隙至少部分地限定在第二加强件和中间结构之间。
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公开(公告)号：US11760463B2
公开(公告)日：2023-09-19
申请号：US17376134
申请日：2021-07-14
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick B. Stickler
Abstract: 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.
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公开(公告)号：US11685503B2
公开(公告)日：2023-06-27
申请号：US16866193
申请日：2020-05-04
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Waeil M. Ashmawi
CPC classification number: B64C1/064 , B29C53/02 , B29C65/48 , B29C66/729 , B29C70/30 , B29C70/545 , B29L2031/3076 , B64C2001/0072
Abstract: 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.
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