公开(公告)号：US09182267B2

公开(公告)日：2015-11-10

申请号：US13818829

申请日：2011-05-24

申请人： Hiroaki Yamaguchi ,  Yuichiro Kamino

发明人： Hiroaki Yamaguchi ,  Yuichiro Kamino

IPC分类号： G01F23/26

CPC分类号： G01F23/263 ,  G01F23/266 ,  G01F23/268

摘要： A fuel gauge (15) provided with an inner structural body (27) that is formed of an insulator; an outer structural body (23) that is formed of an insulator and disposed on the outer circumference side of the inner structural body (27) over the entire circumference thereof; an inner electrode (29) that is attached to an outer circumferential surface of the inner structural body (27); and an outer electrode (25) that is attached to an inner circumferential surface of the outer structural body (23). The fuel guage measures the capacitance between the inner electrode and the outer electrode and detects the level of fuel that exists between the inner electrode and the outer electrode. The outer structural body is provided with a plurality of outer through-holes (31) that allow electric charge to move from an outer circumferential surface thereof to the outer electrode.

摘要翻译： 一种燃料计（15），其具有由绝缘体形成的内部结构体（27）; 外部结构体（23），其由绝缘体形成并且设置在所述内部结构体（27）的外周侧的整个圆周上; 内部电极（29），其安装在所述内部结构体（27）的外周面上; 以及附接到所述外部结构体（23）的内周面的外部电极（25）。 燃料测量仪测量内部电极和外部电极之间的电容，并检测存在于内部电极和外部电极之间的燃料的水平。 外部结构体设置有多个允许电荷从外周表面移动到外部电极的外部通孔（31）。

公开(公告)号：US20140086387A1

公开(公告)日：2014-03-27

申请号：US14007138

申请日：2011-12-26

申请人： Tatsufumi Aoi ,  Yuichiro Kamino ,  Yasuo Ogi ,  Akira Watanabe ,  Nobuyuki Shigeoka

发明人： Tatsufumi Aoi ,  Yuichiro Kamino ,  Yasuo Ogi ,  Akira Watanabe ,  Nobuyuki Shigeoka

IPC分类号： G01V5/00

CPC分类号： G01V5/0041 ,  H05G1/26 ,  H05G1/32 ,  H05G1/34 ,  H05G2/00

摘要： An object is to emit x-rays having a plurality of different energies and to suppress variations in the energy of the created x-rays. In an x-ray generating apparatus (14) provided in an x-ray inspection apparatus (10), a particle accelerator (20) creates a charged particle beam for generating x-rays having a plurality of different energies, and x-rays are emitted by irradiating a target (22) with the charged particle beam. A single-energy control device (40) controls the particle accelerator (20) for each of the x-rays having different energies on the basis of an x-ray radiation level per unit target current obtained from a measured value of the current flowing in the target (22) and a measured value of the radiation level of x-rays emitted from the target (22), when the target (22) is irradiated with the charged particle beam.

摘要翻译： 目的是发射具有多个不同能量的x射线，并且抑制所产生的X射线的能量的变化。 在设置在X射线检查装置（10）中的x射线产生装置（14）中，粒子加速器（20）产生用于产生具有多个能量的x射线的带电粒子束，并且x射线为 通过用带电粒子束照射靶（22）而发射。 单能量控制装置（40）根据从流入的电流的测量值获得的每单位目标电流的X射线辐射水平来控制具有不同能量的每个X射线的粒子加速器（20） 所述目标（22）和当所述目标（22）被所述带电粒子束照射时从所述目标（22）发射的X射线的辐射水平的测量值。

公开(公告)号：US08678320B2

公开(公告)日：2014-03-25

申请号：US13131063

申请日：2009-06-24

申请人： Hiroaki Yamaguchi ,  Yuichiro Kamino ,  Tooru Hashigami ,  Kazuyuki Oguri

发明人： Hiroaki Yamaguchi ,  Yuichiro Kamino ,  Tooru Hashigami ,  Kazuyuki Oguri

IPC分类号： B64D37/02

CPC分类号： B64D37/32 ,  B64C3/34 ,  B64D45/02

摘要： An aircraft fuel tank that is capable of suppressing the occurrence of sparks on a pipe caused by a lightning current through the pipe during a lightning strike, and also suppressing static electricity charging of a pipe caused by flow electrification generated by the fuel. An aircraft fuel tank (1) in which a storage section is formed using a conductive upper skin (5), a conductive lower skin (7) and conductive spars (9), the tank comprising: pipes inside the tank, such as a refuel pipe (17), an engine feed pipe (19) and an inert gas pipe (21), which are disposed inside the storage section and are earthed (27) at a plurality of locations, and pipe outer surface layers (31) having semiconductor properties that are formed in an integrated manner on the outer surfaces of the pipes inside the tank such as the replenishing pipe (17), the supply pipe (19) and the gas pipe (21).

摘要翻译： 一种飞机燃料箱，其能够抑制由于在雷击期间通过管道的雷电流引起的管道上的火花的发生，并且还抑制由燃料产生的流动电气引起的管道的静电充电。 一种飞机燃料箱（1），其中使用导电上皮（5），导电下皮（7）和导电柱（9）形成存储部分，所述罐包括：罐内的管，例如加油 管道（17），发动机供给管（19）和惰性气体管道（21），其设置在存储部分的内部并且在多个位置处接地（27），以及具有半导体的管外表面层 一体地形成在罐内的管子的外表面上的诸如补充管（17），供应管（19）和气管（21）的特性。

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 。

公开(公告)号：US08413929B2

公开(公告)日：2013-04-09

申请号：US12739060

申请日：2009-03-23

申请人： Yuichiro Kamino ,  Kazuyuki Oguri ,  Koichi Nakamura

发明人： Yuichiro Kamino ,  Kazuyuki Oguri ,  Koichi Nakamura

IPC分类号： B64C1/12 ,  B64D45/02

CPC分类号： B64C3/26 ,  B29C65/562 ,  B29C65/564 ,  B29C66/1122 ,  B29C66/43441 ,  B29C66/474 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72321 ,  B29C66/742 ,  B29C70/088 ,  B29C70/885 ,  B29D99/001 ,  B29K2105/06 ,  B29K2305/02 ,  B29K2305/10 ,  B29K2307/00 ,  B29K2309/08 ,  B29K2705/10 ,  B29K2995/0005 ,  B29L2009/003 ,  B29L2031/3082 ,  B29L2031/3085 ,  B64D45/02 ,  F16B33/004 ,  F16B35/06 ,  F16B37/14 ,  B29K2307/04 ,  B29K2079/08 ,  B29K2071/00

摘要： An aircraft assembly is equipped with a lightning protection structure that is not easily destroyed by lightning current and that is highly reliable. The aircraft assembly includes a skin in which a CFRP layer serves as a main structure, a shear-tie that supports the skin from the inside, and a fastener that couples the skin and the shear-tie. A copper foil and an outside GRFP layer are provided on an outer surface side of the skin, in this order towards the outside, and a copper paint layer, which contains copper powder, is provided on the outside GFRP layer.

摘要翻译： 飞机组件配有防雷结构，不易受雷击电流的破坏，高可靠性。 飞行器组件包括其中CFRP层用作主要结构的皮肤，从内部支撑皮肤的剪切带以及连接皮肤和剪切带的紧固件。 在外表面侧设置铜箔和外部GRFP层，朝向外侧依次设置有铜箔和外部GRFP层，在外部GFRP层上设置有含有铜粉末的铜涂层。

公开(公告)号：US20120012710A1

公开(公告)日：2012-01-19

申请号：US13258179

申请日：2010-03-17

申请人： Hiroaki Yamaguchi ,  Yuichiro Kamino ,  Koichi Nakamura ,  Tooru Hashigami

发明人： Hiroaki Yamaguchi ,  Yuichiro Kamino ,  Koichi Nakamura ,  Tooru Hashigami

IPC分类号： B64C3/34 ,  B65D90/02 ,  B32B38/00 ,  B32B38/10 ,  B32B38/08

CPC分类号： B64D37/06 ,  B64C3/34 ,  B64D37/32 ,  Y02T50/44

摘要： A composite tank that can suppress electrification, corrosion and strength degradation, a wing comprising the composite tank, and a method for manufacturing the composite tank. The composite tank comprises: a tank body inside which a combustible material is stored, having a first resin portion (11, 12) formed from a fiber reinforced resin and a metal portion formed from a metal material, a second resin portion (22) formed from a fiber reinforced resin, which covers at least those regions on the inner surface of the tank body where the first resin portion (11, 12) adjoins the metal portion, and a plurality of conductive portions (23) that enable charge transfer through the second resin portion (22), from the surface that contacts the combustible material to the first resin portion (11, 12), wherein the fiber in the second resin portion (22) has a higher electrical resistivity than fiber in the first resin portion (11, 12), and the second resin portion (22) forms a layer that isolates the first resin portion (11, 12) from the metal portion.

摘要翻译： 可抑制带电，腐蚀和强度降低的复合罐，包括复合罐的翼，以及制造复合罐的方法。 复合罐包括：储存有可燃材料的罐体，具有由纤维增强树脂形成的第一树脂部分（11,12）和由金属材料形成的金属部分，形成第二树脂部分（22） 至少覆盖在第一树脂部分（11,12）与金属部分相邻的罐体内表面上的那些区域的多个导电部分（23），所述多个导电部分（23）能够通过 第二树脂部分（22）从与可燃材料接触的表面到第一树脂部分（11,12），其中第二树脂部分（22）中的纤维具有比第一树脂部分中的纤维更高的电阻率 11,12），第二树脂部（22）形成将第一树脂部（11,12）与金属部分隔离的层。

公开(公告)号：US20110297790A1

公开(公告)日：2011-12-08

申请号：US13201916

申请日：2010-03-26

申请人： Hiroaki Yamaguchi ,  Yuichiro Kamino ,  Tooru Hashigami ,  Kazuyuki Oguri ,  Koichi Nakamura

发明人： Hiroaki Yamaguchi ,  Yuichiro Kamino ,  Tooru Hashigami ,  Kazuyuki Oguri ,  Koichi Nakamura

IPC分类号： B64D37/06

CPC分类号： B64C3/34 ,  B64D37/32 ,  B64D45/02

摘要： An aircraft fuel tank capable of suppressing electrostatic charging caused, for example, by flow electrification with the fuel. The aircraft fuel tank comprises an upper skin (5) and a lower skin (7) that exhibit conductivity and form a portion of a container for storing fuel, an internal structure (19) formed from a metal, and an inner surface layer (15) which has semiconductor properties or insulating properties and is formed in an integral manner on the inner surfaces of the upper skin (5) and the lower skin (7) in a location where the internal structure (19) contacts the upper skin (5) and the lower skin (7), and in the surrounding portion thereof, wherein the inner surface layer (15) is formed, at least in the surrounding portion, from a material having semiconductor properties.

摘要翻译： 能够抑制静电充电的飞机燃料箱，例如通过与燃料的流动通电。 飞机燃料箱包括表现导电性并形成用于储存燃料的容器的一部分的上皮（5）和下皮（7），由金属形成的内部结构（19）和内表面层（15） ），其具有半导体性质或绝缘性能，并且在内部结构（19）接触上皮肤（5）的位置中一体地形成在上皮肤（5）和下皮肤（7）的内表面上， 和下表皮（7），并且在其周围部分中，至少在周围部分中，由具有半导体特性的材料形成内表面层（15）。

公开(公告)号：US20110226896A1

公开(公告)日：2011-09-22

申请号：US12940267

申请日：2010-11-05

申请人： Masahiro BESSHO ,  Wataru NISHIMURA ,  Naomoto ISHIKAWA ,  Yuichiro KAMINO ,  Toshikatsu NOHARA ,  Toru HASHIGAMI ,  Tamaki Tsuzuki

发明人： Masahiro BESSHO ,  Wataru NISHIMURA ,  Naomoto ISHIKAWA ,  Yuichiro KAMINO ,  Toshikatsu NOHARA ,  Toru HASHIGAMI ,  Tamaki Tsuzuki

IPC分类号： B64D45/02 ,  B64C1/00 ,  F16B35/00

CPC分类号： B64D45/02 ,  F16B37/14 ,  F16B37/145

摘要： A lightning-resistant fastener, a cap, a fastener member, and a method for attaching the lightning-resistant fastener are provided, which enhance workability and quality stability besides reliably securing an insulating property, and can lead to enhancement in safety of an airframe and reduction in manufacturing cost. A head portion 25b of a fastener main body 25 includes a head cap 50, and a shaft portion 25s of the fastener main body 25 includes a shaft cap 30, whereby a direct strike of lightning to a fastener member 24, and occurrence of an arc discharge from the fastener member 24 in the case of a lightning strike can be suppressed. A hole 52 is formed in the head cap 50, and a thread groove 52a is formed in the hole 52, whereby the head cap 50 can be reliably and easily positioned and attached to the fastener member 24.

摘要翻译： 提供防雷紧固件，盖，紧固件和用于安装防雷紧固件的方法，除了可靠地确保绝缘性能之外，还提高了加工性和质量稳定性，并且可以提高机身的安全性， 降低制造成本。 紧固件主体25的头部25b包括头盖50，并且紧固件主体25的轴部25s包括轴帽30，由此直接撞击紧固件24并发生弧 可以抑制在雷击的情况下从紧固件24排出。 在头盖50中形成孔52，并且在孔52中形成有螺纹槽52a，由此能够可靠且容易地将头盖50定位并附接到紧固件24。

公开(公告)号：US20090173828A1

公开(公告)日：2009-07-09

申请号：US12227642

申请日：2007-06-11

申请人： Kazuyuki Oguri ,  Yuichiro Kamino

发明人： Kazuyuki Oguri ,  Yuichiro Kamino

IPC分类号： B64C1/12 ,  F16B1/00

CPC分类号： F16B33/004 ,  B29C65/562 ,  B29C65/564 ,  B29C66/1122 ,  B29C66/45 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/723 ,  B29C66/742 ,  B29K2305/00 ,  B29K2305/02 ,  B29K2307/00 ,  B29K2309/08 ,  B29K2995/0005 ,  B29K2995/0007 ,  B29L2009/00 ,  B29L2031/3076 ,  B29L2031/3082 ,  B29L2031/3085 ,  F16B35/06 ,  B29K2307/04 ,  B29K2081/04 ,  B29K2079/08 ,  B29K2067/003 ,  B29K2067/00 ,  B29K2023/12

摘要： A fastener, of which severe strength is demanded and which can also be applied to a location, in which a flush surface equipment is taken into consideration, and which can be manufactured readily and quickly and reduced in manufacturing cost, is provided. A fastener (1) joins a skin of an airplane and a structural material positioned inside the skin and one end surface of a flush head (3) is covered by an insulator layer (5).

摘要翻译： 提供了一种紧固件，其具有强大的强度，并且还可以应用于其中考虑到冲洗表面设备并且可以容易且快速地制造并且制造成本降低的位置。 紧固件（1）连接飞机的皮肤和位于皮肤内部的结构材料，并且冲洗头（3）的一个端面被绝缘体层（5）覆盖。

公开(公告)号：US20070081874A1

公开(公告)日：2007-04-12

申请号：US11529244

申请日：2006-09-29

申请人： Yuichiro Kamino ,  Kazuyuki Oguri ,  Makoto Senda ,  Takahiro Sekigawa ,  Akiko Inoue

发明人： Yuichiro Kamino ,  Kazuyuki Oguri ,  Makoto Senda ,  Takahiro Sekigawa ,  Akiko Inoue

IPC分类号： F16B37/14

CPC分类号： B64D45/02 ,  F16B11/00 ,  F16B35/06 ,  F16B37/14 ,  F16B2001/0064

摘要： There is provided a fastener able to prevent damage due to environmental factors such as ultraviolet rays, and impact from sanddust, lumps of ice, and raindrops without obstructing a flow of electric shock current that flows along a top surface of an outer skin. The fastener connects an outer skin of an aircraft to a structural member positioned inside this outer skin, and is provided with a dielectric layer arranged to cover one end surface of a head section, and a conductive layer arranged to cover one end surface of this dielectric layer.

摘要翻译： 提供了一种紧固件，其能够防止由于诸如紫外线的环境因素以及来自沙尘，冰块和雨滴的冲击而造成的损坏，而不会阻碍沿着外皮的顶表面流动的电击电流。 紧固件将飞行器的外皮连接到位于该外皮内部的结构构件，并且设置有布置成覆盖头部的一个端面的介电层和布置成覆盖该电介质的一个端面的导电层 层。