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公开(公告)号：US20220033055A1
公开(公告)日：2022-02-03
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：US10442153B2
公开(公告)日：2019-10-15
申请号：US15852912
申请日：2017-12-22
Applicant: The Boeing Company
Inventor： John M. Shinozaki , Patrick B. Stickler , Jerry D. Chungbin
Abstract: Provided are stiffened stringer panels with integrated indexing stacks. An example composite panel comprises a skin member having an inner surface. An index for positioning a support tool comprises a first set and second set of layered laminate stacks coupled to the inner surface such that a channel is formed between the first and second set of layered laminate stacks. The first and second set of layered laminate stacks is configured to cradle a support tool in the channel to automatically align the support tool relative to the panel. A stringer may include a cap portion that extends from the first set to the second set of layered laminate stacks to form flange portions on the inner surface of the skin member. The index and the skin member may be co-cured or co-bonded.
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公开(公告)号：US11878793B2
公开(公告)日：2024-01-23
申请号：US17387193
申请日：2021-07-28
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Patrick B. Stickler
IPC: B64C3/00 , B29C70/00 , B29D99/00 , B64C3/20 , B64C3/26 , B29C70/08 , B29C70/38 , B64C3/18 , B29L31/30
CPC classification number: B64C3/20 , B29C70/086 , B29C70/386 , B29D99/0014 , B64C3/182 , B64C3/26 , B29L2031/3085
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：US11623731B2
公开(公告)日：2023-04-11
申请号：US16995298
申请日：2020-08-17
Applicant: The Boeing Company
Abstract: Aircraft, aircraft wings and associated shear ties are disclosed. An example apparatus includes a first panel coupled to a second panel to define a wing box; a rib disposed chordwise within the wing box; and a stringer disposed spanwise within the wing box immediately adjacent at least one of the first panel or the second panel, the rib including a shear tie including first and second legs extending in opposite directions, the first and second legs to be coupled to at least one of the first panel, the second panel, or the stringer.
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公开(公告)号：US11613341B2
公开(公告)日：2023-03-28
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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Patent Agency Ranking
公开(公告)号：US20190016436A1
公开(公告)日：2019-01-17
申请号：US15647722
申请日：2017-07-12
Applicant: THE BOEING COMPANY
Inventor： Patrick B. Stickler , Forouzan Behzadpour
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：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：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：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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