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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：US11511847B2
公开(公告)日：2022-11-29
申请号：US15471422
申请日：2017-03-28
Applicant: The Boeing Company
Inventor： Steven P. Walker , Gregory M. Santini , Gary D. Oakes , Patrick B. Stickler
Abstract: A skin panel configured for attachment to an aircraft structure is constructed of a composite material and has a continuous, smooth outer surface; a continuous, smooth inner surface that is configured for attachment to an aircraft structure; a peripheral edge that extends entirely around the skin panel and has a continuous, smooth surface and a plurality of cavities inside the material of the skin panel. The cavities reduce the weight of the skin panel without significantly detracting from the compression strength and tensile strength of the skin panel.
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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：US11273622B2
公开(公告)日：2022-03-15
申请号：US15708894
申请日：2017-09-19
Applicant: The Boeing Company
Inventor： Patrick B. Stickler
Abstract: A stiffening element that includes one or more integral current flowpaths may include: a first layer including carbon-fiber-reinforced thermoplastic plies; a second layer including one or more glass-fiber-reinforced thermoplastic plies; and/or a third layer including aluminum. The third layer may form an outer surface of the stiffening element. The third layer may form at least part of the one or more integral current flowpaths. A method of using a stiffening element that comprises one or more integral current flowpaths as part of a current return network for a stiffened structure may include: selecting the stiffening element that includes a first layer including carbon-fiber-reinforced thermoplastic plies, a second layer including one or more glass-fiber-reinforced thermoplastic plies, and/or a third layer including aluminum; and/or routing current from the current return network through the one or more integral current flowpaths of the selected stiffening element.
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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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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：US20190193371A1
公开(公告)日：2019-06-27
申请号：US15852912
申请日：2017-12-22
Applicant: The Boeing Company
Inventor： John M. Shinozaki , Patrick B. Stickler , Jerry D. Chungbin
CPC classification number: B32B3/28 , B32B5/10 , B32B37/0076 , B32B37/06 , B32B2305/076 , B32B2398/10 , B32B2605/18 , B64C3/182 , Y10T428/24174 , Y10T428/24182
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：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：US20200377193A1
公开(公告)日：2020-12-03
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：US10745103B2
公开(公告)日：2020-08-18
申请号：US15610598
申请日：2017-05-31
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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