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1. 发明申请

US20090288602A1 Electrode and Vacuum Processing Apparatus 审中-公开
标题翻译：电极和真空处理设备
公开(公告)号：US20090288602A1
公开(公告)日：2009-11-26
申请号：US12087071
申请日：2007-03-20
申请人： Kouji Satake , Satoshi Sakai , Atsuhiro Iyomasa , Toshiya Watanabe , Hideo Yamakoshi , Toshiaki Monaka
发明人： Kouji Satake , Satoshi Sakai , Atsuhiro Iyomasa , Toshiya Watanabe , Hideo Yamakoshi , Toshiaki Monaka
IPC分类号： C23C16/54
CPC分类号： H01J37/32541 , C23C16/4412 , C23C16/45578 , C23C16/509 , H01J37/3244 , H05H1/46 , H05H2001/466
摘要： An electrode and a vacuum processing apparatus are provided that are capable of improving the film deposition rate and the uniformity of the distribution of the deposited film. The electrode includes a plurality of electrodes (17A, 17B) extending from positions arranged at a predetermined interval along a surface of a substrate to be processed (3). Buffer chambers (25) each extend along and between two of the plurality of electrodes (17A, 17B). A plurality of first gas injection holes (27) are arranged in the direction in which the electrodes (17A, 17B) extend and which supply a reactant gas into the buffer chamber (25). A second gas injection hole (23) has a slit form extending in the direction in which the electrodes (17A, 17B) extend, and which supplies the reactant gas from the buffer chamber (25) toward the substrate to be processed (3).
摘要翻译：提供了能够提高成膜速度和沉积膜的分布均匀性的电极和真空处理装置。电极包括沿着待处理基板（3）的表面以预定间隔布置的位置延伸的多个电极（17A，17B）。缓冲室（25）各自沿着多个电极（17A，17B）中的两个延伸。多个第一气体喷射孔（27）沿电极（17A，17B）延伸的方向排列，并将反应气体供应到缓冲室（25）中。第二气体注入孔（23）具有沿电极（17A，17B）延伸的方向延伸的狭缝形状，并且将缓冲室（25）的反应气体朝向待处理基板（3）供给。

2. 发明授权

US08587916B2 Lightning protection fastener, aircraft assembly, and method of manufacturing aircraft assembly component 有权
标题翻译：防雷紧固件，飞机组件和制造飞机组件的方法
公开(公告)号：US08587916B2
公开(公告)日：2013-11-19
申请号：US13420008
申请日：2012-03-14
申请人： Hideo Yamakoshi , Yuichiro Kamino , Yuji Asahara , Yasunori Watanabe , Atsuhiro Iyomasa , Toru Hashigami , Kohei Murakami , Tomonori Okumura
发明人： Hideo Yamakoshi , Yuichiro Kamino , Yuji Asahara , Yasunori Watanabe , Atsuhiro Iyomasa , Toru Hashigami , Kohei Murakami , Tomonori Okumura
IPC分类号： H05F3/00
CPC分类号： B64D45/02 , F16B5/0258 , F16B43/001
摘要： A long-life lightning protection fastener or the like to prevent explosion for aircrafts at low cost is provided, the fastener having a light weight, ensuring sufficient lightning protection, and having extremely less failures and high reliability. A ring-shaped ring member 40A made of resin is mounted on a collar 26. This ring member 40A is interposed between a member 22 and the collar 26 and is in intimate contact with both of the member 22 and the collar 26, thereby sealing an interface with the member 22 for sealing and preventing the occurrence of an arc at an outer perimeter edge of the collar 26.
摘要翻译：提供了一种长寿命防雷紧固件等，以便以低成本防止飞机爆炸，该紧固件具有重量轻，确保足够的防雷保护，并具有极少的故障和高的可靠性。由树脂制成的环形环构件40A安装在套环26上。该环件40A插入在构件22和套环26之间，并且与构件22和套环26两者紧密接触，从而密封与构件22接合，用于密封并防止在套环26的外周边缘处发生电弧。

3. 发明授权

US08711541B2 Lightning-protective explosion-preventive fastener 有权
标题翻译：防雷防爆紧固件
公开(公告)号：US08711541B2
公开(公告)日：2014-04-29
申请号：US13432649
申请日：2012-03-28
申请人： Soichiro Umemoto , Hideo Yamakoshi , Atsuhiro Iyomasa , Toru Hashigami
发明人： Soichiro Umemoto , Hideo Yamakoshi , Atsuhiro Iyomasa , Toru Hashigami
IPC分类号： H05F3/00
CPC分类号： B64D45/02
摘要： In an insulating cover 50A according to the present invention, a dimension of each of an outer-circumferential-side cylindrical part 50c and an inner-circumferential-side cylindrical part 50b fitting in step parts 40 and 41 in an axial direction of a fastener body 25 is set large with respect to a tip covering part 50a covering a tip surface 26a of a fastening member 26. As a result, on an outer circumferential side and an inner circumferential side of the fastening member 26, a distance from a member 22 is sufficiently ensured by the cylindrical part 50b and 50c. The tip covering part 50a is thinner than the cylindrical part 50B and 50c. Therefore, when the fastener body 25 and the fastening member 26 are fastened together, the amount of deformation of the tip covering part 50a in a thickness direction can be made small.
摘要翻译：在根据本发明的绝缘盖50A中，沿着紧固件主体的轴向安装在台阶部40和41中的外周侧圆筒部50c和内周侧圆筒部50b的尺寸 25相对于覆盖紧固部件26的前端面26a的顶部覆盖部50a设定得较大。结果，在紧固部件26的外周侧和内周侧，与部件22的距离为由圆柱形部分50b和50c充分确保。尖端覆盖部50a比圆筒部50B，50c薄。因此，当紧固件主体25和紧固构件26紧固在一起时，能够使顶部覆盖部50a在厚度方向上的变形量变小。

4. 发明授权

US08634177B2 Coupling structure for airframe components 有权
标题翻译：机身部件联轴器结构
公开(公告)号：US08634177B2
公开(公告)日：2014-01-21
申请号：US13418865
申请日：2012-03-13
申请人： Koji Kawahara , Hideo Yamakoshi , Yuichiro Kamino , Atsuhiro Iyomasa , Toru Hashigami
发明人： Koji Kawahara , Hideo Yamakoshi , Yuichiro Kamino , Atsuhiro Iyomasa , Toru Hashigami
IPC分类号： H02H1/04 , H02H3/22
CPC分类号： H01R4/06 , B64C3/34 , B64D45/02 , F16B5/02 , F16B15/02 , F16B37/14 , F16B2001/0064 , H05H3/02
摘要： Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.
摘要翻译：提供了能够确保足够的防雷能力的机身部件的联接结构。在机翼表面面板21A和21B之间的每个紧固件24周围形成由导电材料制成的导电图案部分40。导电图案部40例如形成在机翼面板21A和翼面板21B彼此抵接的平面上的各孔21c，21d的周围。然后，通过紧固件24的紧固力将导电图案部40推压到翼面21A和翼面板21B上，由此能够实现翼面21A和翼面面板21B之间的导电。

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