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1. 发明申请

US20070000596A1 Methods of Forming Metal Foil Ply Replacement in Composite Structures 有权
标题翻译：在复合结构中形成金属箔层更换方法
公开(公告)号：US20070000596A1
公开(公告)日：2007-01-04
申请号：US11530582
申请日：2006-09-11
申请人： Willard Westre , David Evans , Edward Li , Marc Piehl , Eric Sager
发明人： Willard Westre , David Evans , Edward Li , Marc Piehl , Eric Sager
IPC分类号： B29C70/00
CPC分类号： B32B15/08 , B32B3/14 , B32B7/12 , B32B38/08 , B32B2260/021 , B32B2260/046 , Y02T50/43 , Y10T156/1089 , Y10T156/109 , Y10T156/1092 , Y10T156/1093 , Y10T428/1234 , Y10T428/12444 , Y10T428/19 , Y10T428/192 , Y10T428/197 , Y10T428/24752
摘要： Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The lamina includes a ply of fiber-reinforced polymer that extends between the first face and the second face and has an interior edge. The interior edge defines at least one cutout. A ply of metal foil extends between the first face and the second face substantially from the interior edge filling the at least one cutout.
摘要翻译：公开了层合结构及其形成方法。在一个实施方案中，层压结构包括金属 - 聚合物复合层。金属 - 聚合物复合薄片具有间隔开的第一表面和第二表面，并且延伸到末端边缘。薄片包括在第一面和第二面之间延伸并具有内部边缘的纤维增强聚合物层。内部边缘限定至少一个切口。一层金属箔基本上从填充至少一个切口的内边缘在第一面和第二面之间延伸。

2. 发明申请

US20060214058A1 Integrated aircraft structural floor 有权
标题翻译：一体化飞机结构地板
公开(公告)号：US20060214058A1
公开(公告)日：2006-09-28
申请号：US11086307
申请日：2005-03-23
申请人： Willard Westre , David Evans
发明人： Willard Westre , David Evans
IPC分类号： B64C1/00
CPC分类号： B64C1/18 , B61D17/10
摘要： A number of integrated floor structures made of lightweight composite materials for use in an aircraft are disclosed. Generally, each of such floors includes a top-layer skin, a bottom-layer skin disposed below the top-layer skin and a first structural core disposed between the top-layer skin and the bottom-layer skin, the first structural core being composed of a honeycomb composite material. One or more denser structural cores can also be incorporated at strategic locations.
摘要翻译：公开了一些用于飞机的由轻质复合材料制成的综合地板结构。通常，每个这样的地板包括顶层皮肤，设置在顶层皮肤下方的底层皮肤和设置在顶层皮肤和底层皮肤之间的第一结构芯，第一结构芯组成的蜂窝复合材料。一个或多个更密集的结构核心也可以并入战略位置。

3. 发明申请

US20060283133A1 Composite reinforcement of metallic structural elements 审中-公开
标题翻译：金属结构件的复合钢筋
公开(公告)号：US20060283133A1
公开(公告)日：2006-12-21
申请号：US11154522
申请日：2005-06-17
申请人： Willard Westre , Leanna Micona , Mark Wilenski , Gary Weber
发明人： Willard Westre , Leanna Micona , Mark Wilenski , Gary Weber
IPC分类号： E04C3/30
CPC分类号： E04C3/29 , E04C2003/0452 , Y10T156/1064
摘要： A selectively reinforced hybrid metal-composite structural element can include a metal element and a composite material. The composite material can be bonded to the metal element by an adhesive layer including a polymer matrix using a radiation curing process, resulting in insubstantial or negligible residual stresses at the bond line between the metal element and the composite element. The structural element also can include a metal closeout cap to provide a barrier from a corrosive atmosphere, and the adhesive layer can encapsulate the composite element to provide a corrosion-resistant barrier between the composite element and the surrounding metal.
摘要翻译：选择性增强的复合金属复合结构元件可以包括金属元素和复合材料。复合材料可以通过使用辐射固化方法的包含聚合物基质的粘合层与金属元件结合，导致在金属元素和复合元素之间的结合线处的非实质性或可忽略的残余应力。结构元件还可以包括金属封闭盖以提供来自腐蚀性气氛的屏障，并且粘合剂层可以包封复合元件以在复合元件和周围金属之间提供耐腐蚀屏障。

4. 发明申请

US20070194175A1 Airplane floor assembly 有权
标题翻译：飞机地板总成
公开(公告)号：US20070194175A1
公开(公告)日：2007-08-23
申请号：US11358503
申请日：2006-02-21
申请人： Max Kismarton , Willard Westre , Stuart Buchan
发明人： Max Kismarton , Willard Westre , Stuart Buchan
IPC分类号： B64C1/18
CPC分类号： B64C1/18 , B64F5/10
摘要： The invention relates to airplane floor assemblies and to methods for their assembly. In one embodiment, an airplane comprises at least one fuselage section and at least one floor section. At least one system component is installed to the floor section prior to installation of the floor section in the fuselage of the airplane. In another embodiment, a floor section adapted to be installed in an airplane includes at least one system component installed to the floor section while it is outside of the airplane. In yet another embodiment, a method is disclosed for assembling an airplane. The method comprises installing at least one system component to a floor section, and installing the floor section into a fuselage section of the airplane.
摘要翻译：本发明涉及飞机地板组件及其组装方法。在一个实施例中，飞机包括至少一个机身部分和至少一个地板部分。在将地板部分安装在飞机的机身之前，至少有一个系统部件安装到地板部分。在另一个实施例中，适于安装在飞机中的地板部分包括在飞机外部安装到地板部分的至少一个系统部件。在另一个实施例中，公开了一种组装飞机的方法。该方法包括将至少一个系统部件安装到地板部分，以及将地板部分安装到飞机的机身部分中。

5. 发明授权

US07115323B2 Titanium foil ply replacement in layup of composite skin 有权
标题翻译：钛箔层叠层复合皮肤层叠
公开(公告)号：US07115323B2
公开(公告)日：2006-10-03
申请号：US10650231
申请日：2003-08-28
申请人： Willard Westre , David W. Evans , Edward Li , Marc J. Piehl , Eric Sager
发明人： Willard Westre , David W. Evans , Edward Li , Marc J. Piehl , Eric Sager
IPC分类号： B32B3/12 , B32B15/08
CPC分类号： B32B15/08 , B32B3/14 , B32B7/12 , B32B38/08 , B32B2260/021 , B32B2260/046 , Y02T50/43 , Y10T156/1089 , Y10T156/109 , Y10T156/1092 , Y10T156/1093 , Y10T428/1234 , Y10T428/12444 , Y10T428/19 , Y10T428/192 , Y10T428/197 , Y10T428/24752
摘要： Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The lamina includes a ply of fiber-reinforced polymer that extends between the first face and the second face and has an interior edge. The interior edge defines at least one cutout. A ply of metal foil extends between the first face and the second face substantially from the interior edge filling the at least one cutout.
摘要翻译：公开了层合结构及其形成方法。在一个实施方案中，层压结构包括金属 - 聚合物复合层。金属 - 聚合物复合薄片具有间隔开的第一表面和第二表面，并且延伸到末端边缘。薄片包括在第一面和第二面之间延伸并具有内部边缘的纤维增强聚合物层。内部边缘限定至少一个切口。一层金属箔基本上从填充至少一个切口的内边缘在第一面和第二面之间延伸。

6. 发明申请

US20050175813A1 Aluminum-fiber laminate 审中-公开
标题翻译：铝纤维层压板
公开(公告)号：US20050175813A1
公开(公告)日：2005-08-11
申请号：US10775564
申请日：2004-02-10
申请人： A. Wingert , Sven Axter , Gary Tuss , Edward Li , Willard Westre , William Grace , Kay Blohowiak , Moe Soleiman , Judy Chen
发明人： A. Wingert , Sven Axter , Gary Tuss , Edward Li , Willard Westre , William Grace , Kay Blohowiak , Moe Soleiman , Judy Chen
IPC分类号： B32B15/14 , B32B15/20 , B32B5/12
CPC分类号： B32B15/14 , B32B3/12 , B32B15/18 , B32B15/20 , B32B2307/714 , B32B2605/18 , Y10T428/24124 , Y10T428/24149
摘要： An exemplary fiber metal laminate includes at least two metallic layers and at least one fiber layer bonded between the two metallic layers. The fiber layer includes a resin matrix and organic polymeric fibers with a modulus of elasticity greater than 270 GPa. The polymeric fibers may include poly diimidazo pyridinylene fibers. The metallic layers may include pre-treated aluminum alloy layers.
摘要翻译：示例性的纤维金属层压体包括至少两个金属层和至少一个结合在两个金属层之间的纤维层。纤维层包括树脂基体和弹性模量大于270GPa的有机聚合物纤维。聚合物纤维可以包括聚二咪唑并吡啶亚麻纤维。金属层可以包括预处理的铝合金层。

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