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公开(公告)号：US10406797B2
公开(公告)日：2019-09-10
申请号：US15646648
申请日：2017-07-11
Applicant: The Boeing Company
Inventor： Kristin L. Krieg , Kay Y. Blohowiak
IPC: B32B15/08 , B32B15/092 , B32B37/14 , B32B37/24 , B32B37/12 , B32B38/00 , B32B15/095 , B32B7/12 , B29C45/14 , B29L31/30 , B29L31/00 , B29K71/00 , B64D45/02 , F16B11/00
Abstract: A method for bonding components is provided. The method includes preparing a surface of a metal component, applying a film adhesive to the prepared surface, forming a thermoplastic component using injection molding such that the film adhesive is positioned between the metal component and the thermoplastic component, and curing the film adhesive.
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12.发明申请THERMOPLASTIC COMPOSITE STRUCTURES EMBEDDED WITH AT LEAST ONE LOAD FITTING AND METHODS OF MANUFACTURING SAME 有权具有至少一个负载配件的热塑复合结构及其制造方法公开(公告)号：US20150321441A1
公开(公告)日：2015-11-12
申请号：US14465911
申请日：2014-08-22
Applicant: The Boeing Company
Inventor： Jeffery Lee Marcoe , Marc Rollo Matsen , Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , John B. Moser , Brett I. Lyons , Moushumi Shome , Kay Y. Blohowiak
CPC classification number: B32B1/08 , B29C33/52 , B29C70/205 , B29C70/462 , B29C2035/0811 , B32B5/024 , B32B2262/106 , B32B2605/08 , B32B2605/12 , B32B2605/18 , D04C1/06
Abstract: Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting. A second load fitting may be positioned on the first plurality of inner layers of thermoplastic composite material.
Abstract translation: 制造嵌入有第一负载配件的热塑性复合管状结构，其包括在可溶性可扩张心轴周围编织第一组多个热塑性复合材料内层的步骤。 第一负载配件位于热塑性复合材料的第一多个内层上。 围绕第一负载配件和心轴编织第二多个热塑性复合材料外层，以便形成嵌入第一负载配件的外包芯。 将所覆盖的心轴安装到匹配的模具组件中并以特定的加热轮廓加热，以便将第一多个热塑性复合材料的内层和第二多个热塑性复合材料的外层与第一负载配件固结，以便 形成嵌入第一负载配件的热塑性复合管状结构。 第二负载配件可以被定位在热塑性复合材料的第一多个内层上。
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公开(公告)号：US11806832B2
公开(公告)日：2023-11-07
申请号：US18173016
申请日：2023-02-22
Applicant: The Boeing Company
Inventor： Eileen O. Kutscha , Kay Y. Blohowiak
IPC: G01N21/35 , B24B49/12 , G01N21/3563 , G01N21/84
CPC classification number: B24B49/12 , G01N21/3563 , G01N2021/3595 , G01N2021/8411 , G01N2021/8444 , G01N2021/8472
Abstract: There is provided a quantitative method for determining a level of a sanding surface preparation of a carbon fiber composite surface, prior to the carbon fiber composite surface undergoing a post-processing operation. The quantitative method includes fabricating a ladder panel of levels of sanding correlating to an amount of sanding of sanding surface preparation standards for a reference carbon fiber composite surface of reference carbon fiber composite structure(s); using surface analysis tools to create target values for quantifying the levels of sanding; measuring, with the surface analysis tools, sanding surface preparation location(s) on the carbon fiber composite surface of a test carbon fiber composite structure, to obtain test result measurement(s); comparing the test result measurement(s) to the levels, to obtain test result level(s); determining if the test result level(s) meet the target values; and determining whether the carbon fiber composite surface is acceptable to proceed with the post-processing operation.
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公开(公告)号：US20210055244A1
公开(公告)日：2021-02-25
申请号：US16544859
申请日：2019-08-19
Applicant: The Boeing Company
Inventor： Eileen O. Kutscha , Tyler J. Zimmerman , Richard A. Miller, II , Kay Y. Blohowiak
Abstract: There is provided a method for determining a quality of an abrasive surface preparation of a composite surface, prior to the composite surface undergoing a post-processing operation. The method includes fabricating levels of abrasive surface preparation standards for a reference composite surface; using a surface analysis tool in the form of an ohm meter, to create target values for quantifying the levels; and measuring, with the surface analysis tool, one or more abrasive surface preparation locations on the composite surface of a test composite structure, to measure one or more of, electrical resistance and surface resistivity, of the composite surface, to obtain test result measurement(s). The method further includes comparing the test result measurement(s) to the levels, to obtain test result level(s); determining if the test result level(s) meet the target value(s); and determining whether the composite surface is acceptable to proceed with the post-processing operation.
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公开(公告)号：US20190077140A1
公开(公告)日：2019-03-14
申请号：US15702098
申请日：2017-09-12
Applicant: The Boeing Company
Inventor： Carrisa A. Pajel , Benjamin P. Hargrave , Hugh C. VanValkenburgh , Darrin Hansen , Kay Y. Blohowiak
Abstract: Methods, systems and apparatuses are disclosed for at least partially curing a light-curable material within a dispenser to obtain an at least partially-cured material and dispensing the at least partially-cured material to a substrate, while retaining substantially all of the light within the dispenser.
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Patent Agency Ranking
公开(公告)号：US20180290183A1
公开(公告)日：2018-10-11
申请号：US16000801
申请日：2018-06-05
Applicant: The Boeing Company
Inventor： Ashley C. Tracey , Anthony M. Westren , Kay Y. Blohowiak , Mark R. Brei , Tyler Jacob Zimmerman , Richard C. Barclay , Tara Kovacs Baker , Yuliya Shafranyuk
IPC: B08B7/00
CPC classification number: B08B7/0042 , B29C33/3835
Abstract: Provided are molds, comprising non-metal base portions and protective optical layers that cover and shield these base portions from laser ablation. For example, a protective optical layer may reflect a laser beam used for ablating the mold. Methods of forming these protective optical layers on non-metal base portions are also provided. In some embodiments, this protective optical layer is the outermost layer exposed to the environment. Alternatively, the protective optical layer may be covered by a release layer. The release layer may be retained or removed during laser ablation. In some embodiments, light emitted by a mold during laser ablation is analyzed to determine performance of its protective optical layer. This feedback may be used to control the laser ablation such as to control orientation of the laser beam relative to the mold.
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公开(公告)号：US09862175B2
公开(公告)日：2018-01-09
申请号：US14795209
申请日：2015-07-09
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley , Marc J. Piehl , Kay Y. Blohowiak , Alan E. Landmann , Richard H. Bossi , Robert L. Carlsen , Gregory Alan Foltz , Geoffrey A. Butler , Liam S. Cavanaugh Pingree , Stephen G. Moore , John Mark Gardner , Robert A. Anderson
IPC: B32B37/00 , B32B37/14 , B32B7/12 , B32B15/00 , B32B15/08 , B32B19/02 , B32B27/00 , B32B3/06 , B29C73/10
CPC classification number: B32B37/144 , B29C73/10 , B32B3/06 , B32B7/12 , B32B15/00 , B32B15/08 , B32B19/02 , B32B27/00 , B32B2250/42 , B32B2260/021 , B32B2305/08 , B32B2307/202 , B32B2307/204 , B32B2307/54 , B32B2307/558 , B32B2311/00 , B32B2398/00 , B32B2405/00 , B32B2605/18 , Y10T29/49208 , Y10T29/49885 , Y10T156/10 , Y10T428/24752 , Y10T428/31678
Abstract: A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.
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公开(公告)号：US20170355181A1
公开(公告)日：2017-12-14
申请号：US15646648
申请日：2017-07-11
Applicant: The Boeing Company
Inventor： Kristin L. Krieg , Kay Y. Blohowiak
IPC: B32B37/14 , B32B15/08 , B32B7/12 , B32B37/12 , B32B38/00 , B29C45/14 , B32B15/092 , B32B37/24 , B32B15/095 , B29K71/00 , B29L31/30 , B29L31/00 , F16B11/00 , B64D45/02
CPC classification number: B32B37/144 , B29C45/14311 , B29K2071/00 , B29L2031/3002 , B29L2031/7288 , B32B7/12 , B32B15/08 , B32B15/092 , B32B15/095 , B32B37/12 , B32B37/24 , B32B38/004 , B32B2037/1253 , B32B2038/0076 , B32B2250/03 , B32B2309/025 , B32B2311/00 , B32B2363/00 , B32B2398/20 , B32B2605/18 , B64D45/02 , F16B11/006 , Y10T428/31529 , Y10T428/31605 , Y10T428/31678 , Y10T428/31681
Abstract: A method for bonding components is provided. The method includes preparing a surface of a metal component, applying a film adhesive to the prepared surface, forming a thermoplastic component using injection molding such that the film adhesive is positioned between the metal component and the thermoplastic component, and curing the film adhesive.
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19.发明授权公开(公告)号：US09718248B2
公开(公告)日：2017-08-01
申请号：US14465911
申请日：2014-08-22
Applicant: The Boeing Company
Inventor： Jeffery Lee Marcoe , Marc Rollo Matsen , Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , John B. Moser , Brett I. Lyons , Moushumi Shome , Kay Y. Blohowiak
CPC classification number: B32B1/08 , B29C33/52 , B29C70/205 , B29C70/462 , B29C2035/0811 , B32B5/024 , B32B2262/106 , B32B2605/08 , B32B2605/12 , B32B2605/18 , D04C1/06
Abstract: Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting. A second load fitting may be positioned on the first plurality of inner layers of thermoplastic composite material.
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公开(公告)号：US09334407B2
公开(公告)日：2016-05-10
申请号：US14078624
申请日：2013-11-13
Applicant: THE BOEING COMPANY
Inventor： Kay Y. Blohowiak , Jacob W. Grob , Joseph H. Osborne
CPC classification number: C09D183/00 , B32B15/08 , B32B27/283 , C09D4/00 , C09D5/08 , C09D5/086 , C23C18/1216 , C23C18/122 , C23C18/1241 , C23C18/1254 , C23C22/74 , C23C2222/20 , Y10T428/256 , Y10T428/31612 , Y10T428/31663 , C08G77/00
Abstract: A coating composition and a method for coating metallic substrates, such as aircraft components exposed to elevated temperatures and/or oxidative conditions. The coating composition includes an aqueous mixture having about 2 vol % to about 50 vol % organosilane, about 0.3 to about 25 vol % metal alkoxide, and about 0.1 to about 30 vol % organic complexing agent. The coating composition may be deposited on a metallic substrate and cured to form a sol-gel coating on the surface of the substrate that is adherent to the substrate, and oxidation and discoloration resistant.
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