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公开(公告)号：US20170211602A1
公开(公告)日：2017-07-27
申请号：US15396812
申请日：2017-01-02
Applicant: The Boeing Company
Inventor： Richard B. Tanner , James Frederick Ackermann
CPC classification number: F16B5/0258 , B23P19/02 , B23P2700/01 , B64D37/005 , B64D45/02 , F16B4/004 , F16B5/02 , F16B33/008 , F16B43/001 , Y10T29/49952 , Y10T29/49963
Abstract: A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.
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公开(公告)号：US11447230B2
公开(公告)日：2022-09-20
申请号：US16777567
申请日：2020-01-30
Applicant: The Boeing Company
Inventor： Richard B. Tanner
Abstract: Apparatuses and methods for aircraft wings, including fuel tank access panel assemblies, are disclosed. For example, an aircraft wing comprises a skin and a load bearing fuel tank access panel assembly fastened to the skin. The skin comprises a fuel tank access panel hole and a first fastener hole. The load bearing fuel tank access panel is configured to bear at least some of a wing bending load and comprises an access panel, a fastener, and a self-locking fastener mating assembly. The access panel comprises a body portion configured to be received in the fuel tank access panel hole, and a lip portion extending over an interior surface of the skin. The lip portion comprises a second fastener hole, and the fastener extends through the first fastener hole and the second fastener hole into the self-locking fastener mating assembly.
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公开(公告)号：US20210237847A1
公开(公告)日：2021-08-05
申请号：US16777567
申请日：2020-01-30
Applicant: The Boeing Company
Inventor： Richard B. Tanner
Abstract: Apparatuses and methods for aircraft wings, including fuel tank access panel assemblies, are disclosed. For example, an aircraft wing comprises a skin and a load bearing fuel tank access panel assembly fastened to the skin. The skin comprises a fuel tank access panel hole and a first fastener hole. The load bearing fuel tank access panel is configured to bear at least some of a wing bending load and comprises an access panel, a fastener, and a self-locking fastener mating assembly. The access panel comprises a body portion configured to be received in the fuel tank access panel hole, and a lip portion extending over an interior surface of the skin. The lip portion comprises a second fastener hole, and the fastener extends through the first fastener hole and the second fastener hole into the self-locking fastener mating assembly.
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公开(公告)号：US20130232883A1
公开(公告)日：2013-09-12
申请号：US13875548
申请日：2013-05-02
Applicant: THE BOEING COMPANY
Inventor： Richard B. Tanner , Brian H. Korenaga , Jeffrey F. Stulc , Ian C. Burford
CPC classification number: B64C1/1461 , B64C1/1446 , E04C2/54 , E05D15/00
Abstract: A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.
Abstract translation: 一种将门安装在飞行器皮肤的进入口中的方法。 复合内门板抵靠皮肤的内表面定位。 复合外门板抵靠皮肤的外表面定位。 多个紧固件通过复合外门板中的紧固件开口安装。 多个紧固件被紧固以在皮肤和复合外门面板之间形成倒角接口。
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公开(公告)号：US10215281B2
公开(公告)日：2019-02-26
申请号：US15146449
申请日：2016-05-04
Applicant: The Boeing Company
Inventor： Charuhas M. Soman , Keith Townsend , Eric D. Blohm , Richard B. Tanner , Mark J. Herzberg , Ralph E. Hardin
Abstract: Disclosed herein is a seal assembly for sealing a gap between a first component and a second component is disclosed. The second component is movable relative to the first component. The seal assembly includes a rub strip and a seal strip. The rub strip includes a seal strip engagement surface having a convex shape. Additionally, the rub strip includes a first component engagement surface that is opposite the seal strip engagement surface and has a concave shape. The seal strip includes a rub strip engagement surface having a convex shape. Furthermore, the seal strip includes a second component engagement surface that is opposite the rub strip engagement surface and has a concave shape. The seal strip engagement surface is harder than the rub strip engagement surface.
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Patent Agency Ranking
公开(公告)号：US20180135683A1
公开(公告)日：2018-05-17
申请号：US15349122
申请日：2016-11-11
Applicant: The Boeing Company
Inventor： Tanni Sisco , Antonio Carlos Rufin , Richard B. Tanner , Dale Winter , Jeffrey Alan Wilkerson , Joe Heeter
Abstract: Systems and methods are provided for fabricating fasteners. One embodiment is an apparatus that includes a fastener. The fastener includes a head, a cylindrical shank that extends from the head and is dimensioned to engage in a fit with a corresponding hole, and a coating that is discontinuously speckled around a circumference of the shank and extends axially along the shank, leaving irregular portions of a surface of the shank exposed. The coating exhibits a higher lubricity than the surface, and the coating exhibits a higher dielectric withstand voltage than the surface.
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公开(公告)号：US20150377279A1
公开(公告)日：2015-12-31
申请号：US14317434
申请日：2014-06-27
Applicant: The Boeing Company
Inventor： Richard B. Tanner , James Frederick Ackermann
CPC classification number: F16B5/0258 , B64D37/005 , B64D45/02 , F16B4/004 , F16B5/02 , F16B33/008 , F16B43/001
Abstract: A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.
Abstract translation: 一种用于在结构中的孔上形成密封的方法和装置。 该装置包括垫圈，套筒和紧固件。 垫圈具有第一通道。 套筒具有第二通道和可扩张部分。 套筒位于洗衣机中的第一通道内。 紧固件具有定位在套筒的第二通道内部的细长部分，以使得套筒的可扩张部分的至少一部分与垫圈形成第一过盈配合。
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公开(公告)号：US10393161B2
公开(公告)日：2019-08-27
申请号：US15396812
申请日：2017-01-02
Applicant: The Boeing Company
Inventor： Richard B. Tanner , James Frederick Ackermann
Abstract: A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.
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公开(公告)号：US20170321804A1
公开(公告)日：2017-11-09
申请号：US15146449
申请日：2016-05-04
Applicant: The Boeing Company
Inventor： Charuhas M. Soman , Keith Townsend , Eric D. Blohm , Richard B. Tanner , Mark J. Herzberg , Ralph E. Hardin
CPC classification number: F16J15/027 , B64C3/56 , F16J15/061 , F16J15/122
Abstract: Disclosed herein is a seal assembly for sealing a gap between a first component and a second component is disclosed. The second component is movable relative to the first component. The seal assembly includes a rub strip and a seal strip. The rub strip includes a seal strip engagement surface having a convex shape. Additionally, the rub strip includes a first component engagement surface that is opposite the seal strip engagement surface and has a concave shape. The seal strip includes a rub strip engagement surface having a convex shape. Furthermore, the seal strip includes a second component engagement surface that is opposite the rub strip engagement surface and has a concave shape. The seal strip engagement surface is harder than the rub strip engagement surface.
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公开(公告)号：US09073618B2
公开(公告)日：2015-07-07
申请号：US13875548
申请日：2013-05-02
Applicant: The Boeing Company
Inventor： Richard B. Tanner , Brian H. Korenaga , Jeffrey F. Stulc , Ian C. Burford
CPC classification number: B64C1/1461 , B64C1/1446 , E04C2/54 , E05D15/00
Abstract: A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.
Abstract translation: 一种将门安装在飞行器皮肤的进入口中的方法。 复合内门板抵靠皮肤的内表面定位。 复合外门板抵靠皮肤的外表面定位。 多个紧固件通过复合外门板中的紧固件开口安装。 多个紧固件被紧固以在皮肤和复合外门面板之间形成倒角接口。
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