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Patent Agency Ranking
公开(公告)号：US20160159453A1
公开(公告)日：2016-06-09
申请号：US14560533
申请日：2014-12-04
Applicant: The Boeing Company
Inventor： Brian H. Korenaga , Robert G. Albers , Ian C. Burtord , William M. Sampedro-Thompson , David W. Evans
CPC classification number: B64C1/064 , B29C67/0007 , B29C70/08 , B29D99/0003 , B29D99/0007 , B32B3/04 , B32B5/26 , B32B7/12 , B32B37/12 , B32B37/18 , B32B2260/021 , B32B2260/023 , B32B2262/101 , B32B2262/106 , B32B2556/00 , B32B2571/00 , B32B2603/00 , B32B2605/18 , B64C2001/0072 , B64D45/00 , B64F5/60 , Y02T50/43
Abstract: Systems and methods provide for edge protection and visual damage indication for a composite blade stringer. According to one aspect, an edge protection and visual indication system may be an edge treatment provided over an outer edge of a web of a composite blade stringer. The edge treatment may include a number of material layers encompassing the outer edge of the web and extending from a first surface of the web to a second surface of the web. The material layers may include a color contrasting layer and fiberglass layers. The material layers may alternatively include two overlapping, pre-cured angles.
Abstract translation: 系统和方法为复合叶片纵梁提供边缘保护和视觉损伤指示。 根据一个方面，边缘保护和视觉指示系统可以是在复合叶片纵梁的腹板的外边缘上提供的边缘处理。 边缘处理可以包括多个材料层，其包围幅材的外边缘并从幅材的第一表面延伸到幅材的第二表面。 材料层可以包括颜色对比层和玻璃纤维层。 材料层可以备选地包括两个重叠的预固化角度。
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2.发明授权公开(公告)号：US09079656B2
公开(公告)日：2015-07-14
申请号：US13767005
申请日：2013-02-14
Applicant: The Boeing Company
Inventor： Brian H. Korenaga , Mark S. Novak
IPC: B64C1/14
CPC classification number: B64C1/1461 , B64C1/1446
Abstract: An access door structure for a wing skin is received in an access hole opening which incorporates a protective glove having a set of mistake resisting features and engaging the periphery of the access hole opening. An inner door seals an interior of the access hole opening and has multiple fastener attachment elements and a set of mating mistake resisting features. An outer door engaged over an exterior of the access hole opening has fastener holes for mating alignment with the fastener attachment elements and receives a plurality of fasteners for engagement of the inner and outer doors.
Abstract translation: 用于机翼皮肤的通道门结构被容纳在入口孔开口中，该开口开口包括具有一组防错特征并且与进入孔开口的周边啮合的防护手套。 内门密封进入孔开口的内部，并具有多个紧固件附接元件和一组配合防错特征。 接合在进入孔开口的外部的外门具有用于与紧固件附接元件配合对准的紧固件孔，并且容纳用于内门和外门接合的多个紧固件。
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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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4.发明申请公开(公告)号：US20140223829A1
公开(公告)日：2014-08-14
申请号：US13767005
申请日：2013-02-14
Applicant: THE BOEING COMPANY
Inventor： Brian H. Korenaga , Mark S. Novak
IPC: B64C1/14
CPC classification number: B64C1/1461 , B64C1/1446
Abstract: An access door structure for a wing skin is received in an access hole opening which incorporates a protective glove having a set of mistake resisting features and engaging the periphery of the access hole opening. An inner door seals an interior of the access hole opening and has multiple fastener attachment elements and a set of mating mistake resisting features. An outer door engaged over an exterior of the access hole opening has fastener holes for mating alignment with the fastener attachment elements and receives a plurality of fasteners for engagement of the inner and outer doors.
Abstract translation: 用于机翼皮肤的通道门结构被容纳在入口孔开口中，该开口开口包括具有一组防错特征并且与进入孔开口的周边啮合的防护手套。 内门密封进入孔开口的内部，并具有多个紧固件附接元件和一组配合防错特征。 接合在进入孔开口的外部的外门具有用于与紧固件附接元件配合对准的紧固件孔，并且容纳用于内门和外门接合的多个紧固件。
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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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