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11. 发明授权

US08360362B2 Aircraft floor and method of assembly 有权
标题翻译：飞机地板和组装方法
公开(公告)号：US08360362B2
公开(公告)日：2013-01-29
申请号：US12056456
申请日：2008-03-27
申请人： Max U. Kismarton , Willard N. Westre , Stuart M. Buchan
发明人： Max U. Kismarton , Willard N. Westre , Stuart M. Buchan
IPC分类号： B64C1/00 , B64C1/18
CPC分类号： B64C1/18 , B64F5/10
摘要： The invention relates to aircraft floor assemblies and to methods for their assembly. In one embodiment, an aircraft 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 aircraft. In another embodiment, a floor section adapted to be installed in an aircraft includes at least one system component installed to the floor section while it is outside of the aircraft. In yet another embodiment, a method is disclosed for assembling an aircraft. The method comprises installing at least one system component to a floor section, and installing the floor section into a fuselage section of the aircraft.
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，适于安装在飞行器中的底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，公开了一种组装飞行器的方法。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行器的机身部分中。

12. 发明授权

US07837148B2 Composite wing-body joint 有权
标题翻译：复合翼体关节
公开(公告)号：US07837148B2
公开(公告)日：2010-11-23
申请号：US11423885
申请日：2006-06-13
申请人： Max U. Kismarton , Willard N. Westre
发明人： Max U. Kismarton , Willard N. Westre
IPC分类号： B64C1/26
CPC分类号： B64C1/26 , B64C3/182 , B64C3/26 , Y10T428/19
摘要： Embodiments of integral composite panels and joints for composite structures are described In one implementation, an integrated panel spanning substantially the entire wingspan of an aircraft, includes at least a center portion and a pair of outwardly projecting wing portions. The portions may include a skin formed from successive layers or plies of composite material which overlap and offset at the joint between respective sections creating a pad-up area to carry loads between the portions. In a particular implementation, the skin is laid over one or more structural stringers which are transitioned into the joints between sections such as by tapering of the thickness and/or stiffness of the stringer.
摘要翻译：在一个实现方案中，跨越飞行器的基本上整个翼展的集成面板包括至少一个中心部分和一对向外突出的翼部分。这些部分可以包括由复合材料的连续层或层组成的表皮，其在相应部分之间的接合处重叠和偏移，形成用于在部分之间承载载荷的垫区。在一个特定的实施方式中，将皮肤放置在一个或多个结构纵梁上，这些结构纵梁过渡到部分之间的关节，例如通过使纵梁的厚度和/或刚度变细。

13. 发明申请

US20100243803A1 INTEGRATED AIRCRAFT FLOOR WITH LONGITUDINAL BEAMS 有权
标题翻译：一体化飞机地板与长期床
公开(公告)号：US20100243803A1
公开(公告)日：2010-09-30
申请号：US12411615
申请日：2009-03-26
申请人： Willard N. Westre , Kevin M. Retz
发明人： Willard N. Westre , Kevin M. Retz
IPC分类号： B64C1/18
CPC分类号： B64C1/18
摘要： An integrated floor for an aircraft fuselage includes a composite panel forming a floor surface and composite beams bonded to the floor panel. The beams extend longitudinally within the fuselage and support the floor.
摘要翻译：用于飞行器机身的集成地板包括形成地板表面的复合板和结合到地板镶板的复合梁。梁在机身内纵向延伸并支撑地板。

14. 发明申请

US20090084899A1 COMPOSITE WING-BODY JOINT 有权
标题翻译：复合机身接头
公开(公告)号：US20090084899A1
公开(公告)日：2009-04-02
申请号：US11423885
申请日：2006-06-13
申请人： Max U. Kismarton , Willard N. Westre
发明人： Max U. Kismarton , Willard N. Westre
IPC分类号： B64C3/26
CPC分类号： B64C1/26 , B64C3/182 , B64C3/26 , Y10T428/19
摘要： Embodiments of integral composite panels and joints for composite structures are described In one implementation, an integrated panel spanning substantially the entire wingspan of an aircraft, includes at least a center portion and a pair of outwardly projecting wing portions. The portions may include a skin formed from successive layers or plies of composite material which overlap and offset at the joint between respective sections creating a pad-up area to carry loads between the portions. In a particular implementation, the skin is laid over one or more structural stringers which are transitioned into the joints between sections such as by tapering of the thickness and/or stiffness of the stringer.
摘要翻译：在一个实现方案中，跨越飞行器的基本上整个翼展的集成面板包括至少一个中心部分和一对向外突出的翼部分。这些部分可以包括由复合材料的连续层或层组成的表皮，其在相应部分之间的接合处重叠和偏移，形成用于在部分之间承载载荷的垫区。在一个特定的实施方式中，将皮肤放置在一个或多个结构纵梁上，这些结构纵梁过渡到部分之间的关节，例如通过使纵梁的厚度和/或刚度变细。

15. 发明授权

US5866272A Titanium-polymer hybrid laminates 失效
公开(公告)号：US5866272A
公开(公告)日：1999-02-02
申请号：US585304
申请日：1996-01-11
申请人： Willard N. Westre , Heather C. Allen-Lilly , Donald J. Ayers , Samuel E. Cregger , David W. Evans , Donald L. Grande , Daniel J. Hoffman , Mark E. Rogalski , Robert J. Rothschilds
发明人： Willard N. Westre , Heather C. Allen-Lilly , Donald J. Ayers , Samuel E. Cregger , David W. Evans , Donald L. Grande , Daniel J. Hoffman , Mark E. Rogalski , Robert J. Rothschilds
IPC分类号： B32B15/08 , B64C1/00 , B64C1/12 , B64C30/00 , B32B3/12
CPC分类号： B64C30/00 , B32B15/08 , B32B15/14 , B32B3/12 , B32B37/146 , B32B5/02 , B32B5/12 , B32B7/005 , B64C1/12 , B64C3/26 , B32B2250/42 , B32B2255/06 , B32B2260/023 , B32B2260/046 , B32B2262/10 , B32B2262/106 , B32B2305/076 , B32B2307/306 , B32B2307/54 , B32B2307/552 , B32B2307/714 , B32B2311/18 , B32B2605/18 , B64C2001/0072 , Y02T50/433 , Y10T428/1234 , Y10T428/12431 , Y10T428/12444 , Y10T428/12569 , Y10T428/12806 , Y10T428/24165 , Y10T428/249942 , Y10T428/26 , Y10T428/31678
摘要： The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.

16. 发明授权

US5171099A Apparatus to attach a sandwich panel 失效
标题翻译：用于连接夹芯板的装置
公开(公告)号：US5171099A
公开(公告)日：1992-12-15
申请号：US608005
申请日：1990-11-01
申请人： Willard N. Westre
发明人： Willard N. Westre
IPC分类号： F16B5/01
CPC分类号： F16B5/01 , Y10T403/4697
摘要： An apparatus for attaching a sandwich panel to another structure. A hollow pin passes through the panel near the edge to be joined to the structure. A bolt, passing through the edge of the panel, and barrel nut, inside the hollow of the pin, are used to draw the edge of the panel against a flange attached to the structure. The panel may be reinforced with doublers or an end cap.
摘要翻译：一种用于将夹层板连接到另一结构的装置。空心针穿过靠近边缘的面板，以连接到结构。使用穿过板的边缘的螺栓和在销的中空部内的桶形螺母将板的边缘拉向附接到结构的凸缘。面板可以用双层或端盖加固。

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