专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US11154898B2 Fuel tank sealant application system 有权
公开(公告)号：US11154898B2
公开(公告)日：2021-10-26
申请号：US15927433
申请日：2018-03-21
申请人： Honda Patents & Technologies North America, LLC
发明人： Kevin Michael Wilkens , Brian Duncan Ray , John Jeffrey Carter , Michael Dale Bullard
IPC分类号： B05C11/10 , B64F5/10 , B05B13/04 , B25J11/00 , B64C3/34 , F16J15/14
摘要： An application system includes one or more flow control mechanisms controlling a flow path to a dispenser device, one or more position control mechanisms controlling a position of the dispenser device, and a memory device storing data associated with the flow control mechanisms, the position control mechanisms, one or more target areas, and computer-executable instructions. The computer-executable instructions may be executed to identify a target area, actuate the position control mechanisms to move the dispenser device toward the target area, actuate the flow control mechanisms to channel the sealant materials toward the dispenser device, dispense one or more first shots of the sealant materials onto the target area using the dispenser device for forming a dollop at the target area, and dispense one or more second shots of the sealant materials onto the target area using the dispenser device for forming a sealant layer that overlies the dollop.

2. 发明申请

US20140339365A1 WINDOW OF AN AIRCRAFT 有权
标题翻译：飞机窗口
公开(公告)号：US20140339365A1
公开(公告)日：2014-11-20
申请号：US14274825
申请日：2014-05-12
申请人： Honda Patents & Technologies North America, LLC
发明人： Michimasa Fujino , Yasuhiro Homma
IPC分类号： B64C1/14 , B64D11/02
CPC分类号： B64C1/1484 , B64C1/1492 , B64D11/02
摘要： An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.
摘要翻译：飞机包括机身，其包括沿着机身的纵向方向以预定间隔设置的多个框架构件和沿纵向大致直线延伸的多个纵梁。机身定义了飞机内饰。机舱位于机身内部。隔间定义一个内部区域。第一个窗户组件安装到机身的上部，以将日光引入内部区域。第一窗组件的侧面是多个框架构件的相邻框架构件和多个桁条的相邻桁条。第一窗组件包括窗玻璃，内盖和保持架。内盖将日光从窗玻璃引入内部区域。保持架将窗玻璃和内盖固定在机身上。

3. 外观设计

USD688679S1 Display screen portion with icon 有权
公开(公告)号：USD688679S1
公开(公告)日：2013-08-27
申请号：US29403606
申请日：2011-10-07
申请人： Christopher Osborne , Yasuhiro Homma
设计人： Christopher Osborne , Yasuhiro Homma

4. 发明申请

US20130096246A1 Composite Material and Related Methods 审中-公开
标题翻译：复合材料及相关方法
公开(公告)号：US20130096246A1
公开(公告)日：2013-04-18
申请号：US13650804
申请日：2012-10-12
申请人： Honda Patents & Technologies North America, LL
发明人： Eric Walker
IPC分类号： C08K3/04
CPC分类号： C08K3/04 , C08K2201/003 , C08K2201/006
摘要： A composition having a composite material having a polymer with about 1% to about 3% by weight thin-graphite materials dispersed therein; the thin-graphite materials having diameters less than or equal to 2 microns and a surface area greater than or equal to about 300 m2 per gram; and the composite material having a tensile modulus that is at least 25% greater than the unfilled polymer.
摘要翻译：具有复合材料的组合物，其具有聚合物，其中分散有约1％至约3％重量的薄石墨材料; 薄石墨材料具有小于或等于2微米的直径和大于或等于约300平方米/克的表面积; 并且所述复合材料的拉伸模量比未填充的聚合物大至少25％。

5. 发明授权

US08251313B2 Ice protection system for aircraft 有权
标题翻译：飞机防冰系统
公开(公告)号：US08251313B2
公开(公告)日：2012-08-28
申请号：US11256429
申请日：2005-10-21
申请人： Kenichi Goto
发明人： Kenichi Goto
IPC分类号： B64D15/00
CPC分类号： B64D15/00 , B64D27/18
摘要： The ice prevention system of the present invention utilizes, in combination, a de-ice subsystem and anti-ice subsystem in a new configuration on an aircraft with engines located behind its wings. Depending on the vertical location of the engines with respect to the wings, the anti-ice subsystem is configured on an upper or lower portion of a leading edge of the wings. If the engine is located above the wing, the anti-ice system is configured only on a section of the wing aligned with the engine and only on the upper portion of the leading edge. If the engine is located below the wing, the placement of anti-ice system is reversed. The de-ice subsystem is configured on the opposite portion of the leading edge adjacent to the anti-ice subsystem and on the remainder of the leading edge of the wing.
摘要翻译：本发明的防冰系统组合地使用飞机上的新配置的除冰子系统和防冰子系统，其具有位于其翼后面的发动机。取决于发动机相对于机翼的垂直位置，防冰子系统配置在翼的前缘的上部或下部。如果发动机位于机翼上方，则防冰系统仅配置在与发动机对准的机翼的一部分上，并且仅在前缘的上部配置。如果发动机位于机翼下方，则防冰系统的布置相反。除冰子系统配置在与防冰子系统相邻的前缘的相对部分上，以及机翼前缘的其余部分。

6. 发明申请

US20120133200A1 BRAKE SYSTEM AND METHOD 有权
标题翻译：制动系统和方法
公开(公告)号：US20120133200A1
公开(公告)日：2012-05-31
申请号：US13388860
申请日：2011-10-10
申请人： Hiroki Oyama , Michael Joseph Boland
发明人： Hiroki Oyama , Michael Joseph Boland
IPC分类号： B60T13/138 , B60T15/36
CPC分类号： B60T13/686 , B60T8/325 , B60T11/21 , B60T13/12 , B64C25/44 , B64C25/46 , F15B11/003 , F15B13/01 , F15B2211/30515 , F15B2211/3138 , F15B2211/329 , F15B2211/40515 , F15B2211/41527 , F15B2211/428 , F15B2211/455
摘要： A hydraulic system for an aircraft includes a brake operation device, a pressure supply, a reservoir, a shut-off valve, and a wheel brake. The shut-off valve is in fluid communication with and is disposed between the pressure supply and the brake valve. The shut-off valve can include a poppet, a first valve seat and a second valve seat. Movement of the poppet is controlled by operation of the brake operation device. The poppet is movable between a first position where the poppet acts against the first valve seat and a second position where the poppet acts against the second valve seat. In the first position, fluid flow is blocked between the pressure supply and the brake valve through the shut-off valve. In the second position, fluid flow is allowed between the pressure supply and the brake valve through the shut-off valve. The wheel brake is in fluid communication with and downstream from the shut-off valve.
摘要翻译：用于飞机的液压系统包括制动操作装置，压力源，储存器，截止阀和车轮制动器。截止阀与压力供应和制动阀流体连通并设置在压力供应和制动阀之间。截止阀可以包括提升阀，第一阀座和第二阀座。提升阀的运动由制动操作装置的操作控制。提升阀可以在提升阀作用在第一阀座上的第一位置和提升阀作用在第二阀座上的第二位置之间移动。在第一位置，流体通过截止阀在压力供应和制动阀之间被阻塞。在第二位置，允许通过截止阀在压力供应和制动阀之间流体流动。车轮制动器与截止阀流体连通和下游。

7. 再颁专利

USRE46320E1 Aircraft, toy replica, and/or other replicas with surface ornamentation 有权
标题翻译：飞机，玩具复制品和/或具有表面装饰的其他复本
公开(公告)号：USRE46320E1
公开(公告)日：2017-02-28
申请号：US29515390
申请日：2015-01-22
申请人： Honda Patents & Technologies North America, LLC
发明人： Michimasa Fujino , Chris Osborne

8. 发明授权

US09038955B2 Fuel transfer system controlled by float valves 有权
标题翻译：由浮阀控制的燃油传输系统
公开(公告)号：US09038955B2
公开(公告)日：2015-05-26
申请号：US13559227
申请日：2012-07-26
申请人： Kenichi Goto
发明人： Kenichi Goto
IPC分类号： B64D37/14 , B64D37/28
CPC分类号： B64D37/28 , Y10T137/7303
摘要： A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the lower tank, an upper float valve associated with the upper fuel transfer line outlet, and a lower float valve associated with the lower fuel transfer line outlet. The upper fuel transfer line outlet, which is in the lower tank, is in fluid communication with the upper tank. The lower fuel transfer line outlet, which is located in the lower tank, is in fluid communication with the upper tank.
摘要翻译：一种用于飞行器的燃料传输系统，包括上部罐，下部罐，连接上部罐与下部罐的燃料传输线，下部罐中的上部燃料传输线出口，下部罐中的下部燃料传输线出口，与上燃料传输线出口相关联的上浮阀和与下燃料传输线出口相关联的下浮阀。位于下部箱体中的上部燃料传输管路出口与上部箱体流体连通。下部燃料传输线出口位于下部箱体中，与上部箱体流体连通。

9. 发明授权

US08883266B2 Irradiation assisted nucleation of quantum confinements by atomic layer deposition 有权
标题翻译：通过原子层沉积来辐射辅助成核量子限制
公开(公告)号：US08883266B2
公开(公告)日：2014-11-11
申请号：US13915468
申请日：2013-06-11
申请人： The Board of Trustees of the Leland Stanford Junior University , Honda Patents & Technologies North America, LLC
发明人： Timothy P. Holme , Andrei Iancu , Hee Joon Jung , Michael C Langston , Munekazu Motoyama , Friedrich B. Prinz , Takane Usui , Hitoshi Iwadate , Neil Dasgupta , Cheng-Chieh Chao
IPC分类号： C08J7/18 , H01L31/0352 , C23C16/48 , H01L21/02 , B82Y10/00 , H01L31/18
CPC分类号： C23C16/482 , B82Y10/00 , B82Y20/00 , C23C16/48 , C23C16/483 , C23C16/486 , C23C16/487 , H01L21/02532 , H01L21/02568 , H01L21/02601 , H01L21/02603 , H01L21/0262 , H01L31/035209 , H01L31/035218 , H01L31/035227 , H01L31/035236 , H01L31/18 , Y10S977/762 , Y10S977/773 , Y10S977/774
摘要： A method of fabricating quantum confinements is provided. The method includes depositing, using a deposition apparatus, a material layer on a substrate, where the depositing includes irradiating the layer, before a cycle, during a cycle, and/or after a cycle of the deposition to alter nucleation of quantum confinements in the material layer to control a size and/or a shape of the quantum confinements. The quantum confinements can include quantum wells, nanowires, or quantum dots. The irradiation can be in-situ or ex-situ with respect to the deposition apparatus. The irradiation can include irradiation by photons, electrons, or ions. The deposition is can include atomic layer deposition, chemical vapor deposition, MOCVD, molecular beam epitaxy, evaporation, sputtering, or pulsed-laser deposition.
摘要翻译：提供了一种制造量子限制的方法。该方法包括使用沉积设备沉积衬底上的材料层，其中沉积包括在循环之前，循环期间和/或在沉积循环之后照射该层，以改变在该沉积中的量子限制的成核材料层以控制量子限制的尺寸和/或形状。量子限制可以包括量子阱，纳米线或量子点。相对于沉积设备，照射可以就地或离位。照射可以包括光子，电子或离子的照射。沉积可以包括原子层沉积，化学气相沉积，MOCVD，分子束外延，蒸发，溅射或脉冲激光沉积。

10. 发明申请

US20140027575A1 FUEL TRANSFER SYSTEM CONTROLLED BY FLOAT VALVES 有权
标题翻译：燃油转运系统由浮阀控制
公开(公告)号：US20140027575A1
公开(公告)日：2014-01-30
申请号：US13559227
申请日：2012-07-26
申请人： Kenichi Goto
发明人： Kenichi Goto
IPC分类号： B64D37/28
CPC分类号： B64D37/28 , Y10T137/7303
摘要： A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the lower tank, an upper float valve associated with the upper fuel transfer line outlet, and a lower float valve associated with the lower fuel transfer line outlet. The upper fuel transfer line outlet, which is in the lower tank, is in fluid communication with the upper tank. The lower fuel transfer line outlet, which is located in the lower tank, is in fluid communication with the upper tank.
摘要翻译：一种用于飞行器的燃料传输系统，包括上部罐，下部罐，连接上部罐与下部罐的燃料传输线，下部罐中的上部燃料传输线出口，下部罐中的下部燃料传输线出口，与上燃料传输线出口相关联的上浮阀和与下燃料传输线出口相关联的下浮阀。位于下部箱体中的上部燃料传输管路出口与上部箱体流体连通。下部燃料传输线出口位于下部箱体中，与上部箱体流体连通。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式