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1. 发明授权

US4895378A Slidable high-temperature seal 失效
标题翻译：可滑动高温密封
公开(公告)号：US4895378A
公开(公告)日：1990-01-23
申请号：US207337
申请日：1988-06-15
申请人： Charles W. Newquist , Willard N. Westre , Robert A. Burns , Harry W. Dursch
发明人： Charles W. Newquist , Willard N. Westre , Robert A. Burns , Harry W. Dursch
IPC分类号： B64C1/40 , F02C7/042 , F02K1/80
CPC分类号： F02K1/805 , F02C7/042 , Y02T50/672 , Y10S277/936 , Y10T403/52
摘要： A seal for preventing extremely hot gases from passing between a movable engine ramp and an engine splitter wall in a hypersonic aircraft. The seal moves with the engine ramp, in a direction parallel to the surface of the splitter wall. The seal includes a first flange which makes sliding contact with the outer engine ramp surface and is attached to a flexible sealing portion that fills the gap between the ramp and wall. The sealing portion maintains sliding contact with the wall as the gap changes dimension due to variations in the ramp's temperature. The attachment region can be a concave surface to radiate the seal's heat. In a second embodiment, the seal includes a second flange through which the seal is attached to the cooler side of the engine ramp.
摘要翻译：用于防止极高热气体在超音速飞行器中的可动发动机斜坡和发动机分流器壁之间通过的密封件。密封件沿着平行于分流壁表面的方向与发动机斜坡一起移动。该密封件包括与外部发动机斜坡表面滑动接触并附接到填充斜坡和壁之间的间隙的柔性密封部分的第一凸缘。密封部分由于斜坡温度的变化而随着间隙改变尺寸而保持与壁的滑动接触。附接区域可以是凹面以辐射密封件的热量。在第二实施例中，密封件包括第二凸缘，密封件通过第二凸缘连接到发动机斜坡的冷却器侧。

2. 发明授权

US6114050A Titanium-polymer hybrid laminates 有权
标题翻译：钛 - 聚合物混合层压板
公开(公告)号：US6114050A
公开(公告)日：2000-09-05
申请号：US222371
申请日：1998-12-29
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.
摘要翻译：本发明提供了一种适用于超音速民用飞机的混合层压板和混合层压结构的蒙皮板。混合层压板包括钛合金箔层和复合层层的叠层，其被最佳地取向以抵消使用中遇到的力，其结合到中心芯结构，例如钛合金蜂窝体。复合帘布层的增强纤维选自碳和硼，并且纤维在每个帘布层内连续且平行取向。然而，一些层可以与其他层相交角度。然而，在本发明的优选实施方案中，混合层叠体的纤维的绝大多数或全部是在共同的方向上取向的。层压板的外表面包括一层钛箔，用于保护下面的复合材料结构免受环境侵蚀，并受到溶剂的侵蚀等。

3. 发明申请

US20090095413A1 COMPOSITE REINFORCEMENT OF METALLIC STRUCTURAL ELEMENTS 审中-公开
标题翻译：金属结构元件的复合增强
公开(公告)号：US20090095413A1
公开(公告)日：2009-04-16
申请号：US12338293
申请日：2008-12-18
申请人： Willard N. Westre , Leanna M. Micona , Mark S. Wilenski , Gary R. Weber
发明人： Willard N. Westre , Leanna M. Micona , Mark S. Wilenski , Gary R. Weber
IPC分类号： B32B37/00
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. 发明授权

US07491289B2 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的方法
公开(公告)号：US07491289B2
公开(公告)日：2009-02-17
申请号：US11530582
申请日：2006-09-11
申请人： Willard N. Westre , David W Evans , Edward Li , Marc J. Piehl , Eric Sager
发明人： Willard N. Westre , David W Evans , Edward Li , Marc J. Piehl , Eric Sager
IPC分类号： B29C65/00 , B32B37/00 , B32B3/00 , H05K13/04 , E04F13/08 , B64C1/00
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。

5. 发明授权

US07192501B2 Method for improving crack resistance in fiber-metal-laminate structures 失效
标题翻译：提高纤维 - 金属 - 层压结构抗裂性的方法
公开(公告)号：US07192501B2
公开(公告)日：2007-03-20
申请号：US10283546
申请日：2002-10-29
申请人： Willard N. Westre , Leanna M. Micona , Earl E. Van Beek
发明人： Willard N. Westre , Leanna M. Micona , Earl E. Van Beek
IPC分类号： B24B1/00
CPC分类号： B32B15/14 , B32B7/12 , B32B2262/106 , B32B2311/18 , B32B2311/24 , C21D7/06 , C21D2251/02 , Y10T156/1039 , Y10T156/1046 , Y10T428/12993
摘要： A method is provided for altering residual stresses in a fiber-metal-laminate structure. At least a first fiber laminate substrate layer having first and second surfaces is provided. At least a first outer metallic laminate layer having third and fourth surfaces is provided, and the first and fourth surface is provided, and the first and fourth surfaces are bonded together. The third surface is peened, such that the at least first fiber laminate substrate layer is subjected to residual tensile stresses and the at least first outer metallic laminate layer is subjected to residual compression stresses. Peening defines a peened region that extends from the third surface into the at least first outer metallic laminate layer a finite distance that is closer to the third surface than the fourth surface.
摘要翻译：提供了一种用于改变纤维 - 金属 - 层压结构中的残余应力的方法。至少提供具有第一表面和第二表面的第一纤维层叠基底层。至少提供具有第三和第四表面的第一外部金属层压层，并且设置第一和第四表面，并且第一和第四表面粘合在一起。第三表面被喷丸处理，使得至少第一纤维层压基板层受到残余拉伸应力，并且至少第一外金属层压层受到残余压缩应力。喷丸定义了从第三表面延伸到至少第一外金属层压层的喷丸区域，该距离比第四表面更靠近第三表面。

6. 发明授权

US08240606B2 Integrated aircraft floor with longitudinal beams 有权
标题翻译：集成飞机地板纵梁
公开(公告)号：US08240606B2
公开(公告)日：2012-08-14
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。

7. 发明授权

US07938362B2 Airplane floor assembly 有权
标题翻译：飞机地板总成
公开(公告)号：US07938362B2
公开(公告)日：2011-05-10
申请号：US11358503
申请日：2006-02-21
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 , B64C30/00
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。

8. 发明申请

US20080210820A1 AIRCRAFT FLOOR AND METHOD OF ASSEMBLY 有权
标题翻译：飞机地板和装配方法
公开(公告)号：US20080210820A1
公开(公告)日：2008-09-04
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： B64C1/18
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，飞行器包括至少一个机身部分和至少一个底板部分。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。

9. 发明授权

US5445861A Lightweight honeycomb panel structure 失效
标题翻译：轻质蜂窝板结构
公开(公告)号：US5445861A
公开(公告)日：1995-08-29
申请号：US940501
申请日：1992-09-04
申请人： Jefferson F. Newton , Thomas D. Martin , Willard N. Westre , David J. Carbery , Roy Ikegami
发明人： Jefferson F. Newton , Thomas D. Martin , Willard N. Westre , David J. Carbery , Roy Ikegami
IPC分类号： B32B3/12 , B64C1/40 , E04C2/36 , G10K11/172
CPC分类号： G10K11/172 , B32B3/12 , E04C2/365 , Y10T428/236 , Y10T428/24149 , Y10T428/24165 , Y10T428/24273 , Y10T428/24661
摘要： Disclosed is a lightweight honeycomb structure that comprises a top panel (34) and bottom panel (32) and a large-celled honeycomb layer (36) disposed between the top and bottom panels. The honeycomb panel structure according to the present invention can be used in such applications as a sound-absorbing payload shroud for launch vehicles, flooring and walls in aerospace applications, aircraft wings and in structures that will be exposed to high heat. Additionally, a method of making a honeycomb structure of thermoplastic material is disclosed.
摘要翻译：公开了一种轻质蜂窝结构，其包括顶板（34）和底板（32）以及设置在顶板和底板之间的大孔蜂窝层（36）。根据本发明的蜂窝板结构可用于诸如用于运载火箭的吸音有效载荷罩，航空航天应用中的地板和墙壁，飞机机翼和将被暴露于高热的结构中。另外，公开了制造热塑性材料的蜂窝结构体的方法。

10. 发明授权

US4975014A High temperature low thermal expansion fastener 失效
标题翻译：高温低热膨胀紧固件
公开(公告)号：US4975014A
公开(公告)日：1990-12-04
申请号：US401907
申请日：1989-09-01
申请人： Antonio C. Rufin , Willard N. Westre
发明人： Antonio C. Rufin , Willard N. Westre
IPC分类号： F16B1/00 , F16B35/00
CPC分类号： F16B35/00 , F16B2001/0078 , Y10S411/901 , Y10T403/217 , Y10T403/75
摘要： A high-temperature, low-thermal expansion fastener for joining low thermal expansion refractory materials includes a pin with an inset portion on the shank of the pin that forms a head-facing shoulder, at least one shell insert which is seatable about the inset portion, and an internally threaded member which can be screwed onto the threaded outer surface of the shell inserts to maintain the inserts in abutting relationship with the inset portion. Forces within the fastener are transferred from the internally threaded member to the shell inserts which in turn press against the head-facing shoulder on the pin shank to place the shank in tension. The fastener parts, including a spacer, may be selected to compensate for thermal expansion or contraction of the fastened elements.
摘要翻译：一种用于接合低热膨胀耐火材料的高温，低热膨胀紧固件包括销，该销在销的柄上具有形成头朝向的肩部的插入部分，至少一个壳体插入件，其可围绕插入部分以及内螺纹构件，其可以螺纹连接到壳体插入件的螺纹外表面上，以使插入件与插入部分保持邻接关系。紧固件内的力从内螺纹构件转移到壳体插入件，该插入件进而抵靠销柄上的朝向头部的肩部，以使柄处于张力。可以选择包括间隔件的紧固件部件来补偿紧固元件的热膨胀或收缩。

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