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    • 11. 发明专利
    • Heat-pipe embedded honeycomb sandwich panel
    • 热管嵌入式蜂窝三明治板
    • JP2005167233A
    • 2005-06-23
    • JP2004334589
    • 2004-11-18
    • Mitsubishi Electric Corp三菱電機株式会社
    • YAO AKIRA
    • F28D15/02H01L23/427H05K7/20
    • H01L2924/0002H01L2924/00
    • PROBLEM TO BE SOLVED: To provide a honeycomb sandwich panel capable of reducing a space required for wiring a power source line and a signal line connected with an electronic apparatus and mounting the electronic apparatus on the panel with a high density with respect to a heat-pipe embedded honeycomb sandwich panel that is used as a panel for mounting the apparatus of a spacecraft and a satellite and required for demands as a structural material and the heat dissipating plate of the mounted electronic apparatus. SOLUTION: In a heat-pipe embedded honeycomb sandwich panel formed of a honeycomb sandwich panel and a heat pipe 3 embedded in this honeycomb sandwich panel, a power source line 6 and a signal line 7 for an electronic apparatus 5 attached to one surface or both surfaces of the panel are provided in a printed circuit board embedded in the honeycomb sandwich panel. COPYRIGHT: (C)2005,JPO&NCIPI
    • 要解决的问题:提供一种蜂窝夹层板,其能够减少与电子设备连接的电源线和信号线的布线所需的空间,并且将电子设备以相对于高密度的高密度安装在面板上 一种热管嵌入式蜂窝夹层板,其用作用于安装作为结构材料的要求的飞船和卫星的装置的面板以及所安装的电子设备的散热板。 解决方案:在嵌入蜂窝夹层板的蜂窝夹层板和热管3形成的热管嵌入式蜂窝夹层板中,安装有电源线6和电子设备5的信号线7 面板的表面或两个表面设置在嵌入蜂窝夹层板中的印刷电路板中。 版权所有(C)2005,JPO&NCIPI
    • 12. 发明专利
    • Developing radiator and artificial satellite body provided with the same
    • 开发散热器和人造卫星身体
    • JP2003312600A
    • 2003-11-06
    • JP2002116520
    • 2002-04-18
    • Mitsubishi Electric Corp三菱電機株式会社
    • OGUSHI TETSUROISHIKAWA HIROAKIUMEMOTO TOSHIYUKIYAO AKIRA
    • B64G1/50F25B23/00F28D15/02
    • F28D15/0266
    • PROBLEM TO BE SOLVED: To provide developing radiator capable of improving the heat transport capacity of a loop type heat pipe.
      SOLUTION: Among loop type heat pipes 3 connected with a panel arranged in an artificial satellite body 1, a team header pipe 3c comprising branch pipes (uppers steam header pipe 3c
      1 and lower steam header pipe 3c
      2 ) vertically branched to two (heat discharging side and its lower side), a condensation pipe 3d
      1 connecting the upper steam header pipe 3c
      1 and an upper liquid header pipe 3e
      1 , a condensation pipe 3d
      2 connecting the lower steam header pipe 3c
      2 and a lower liquid header pipe 3e
      2 , and a liquid header pipe comprises a branch pipe vertically branched to two (the upper liquid header pipe 3e
      1 and the lower liquid header pipe 3e
      2 ) are buried in the developing radiator 4.
      COPYRIGHT: (C)2004,JPO
    • 要解决的问题:提供能够提高环型热管的传热能力的显影散热器。 解决方案:在与配置在人造卫星体1中的面板连接的环路型热管3中,设有分支管(上部蒸汽总管3c&lt; SB&gt; 1&lt; SB&gt;和下部蒸汽集管 垂直分支到两个(放热侧及其下侧)的冷凝管3d 连接上部蒸汽集管3c 1 ,连接下部蒸汽总管3c 2 的冷凝管3d 和下部液体集管 3e 2 ,并且液体总管包括垂直分支为两个的分支管(上液体总管3e 1 和下液体总管3e 2 < / SB>)埋在发展中的散热器4中。版权所有(C)2004,JPO
    • 13. 发明专利
    • Heat control device for artificial satellite
    • 人造卫星热控制装置
    • JP2003291900A
    • 2003-10-15
    • JP2002104299
    • 2002-04-05
    • Mitsubishi Electric Corp三菱電機株式会社
    • OGUSHI TETSUROISHIKAWA HIROAKIUMEMOTO TOSHIYUKIYAO AKIRA
    • B64G1/50F25D9/00F28D15/02
    • F28D15/0266
    • PROBLEM TO BE SOLVED: To provide a heat control device for an artificial satellite, capable of heat control without consuming any electric energy of the artificial satellite.
      SOLUTION: The heat control device comprises a plurality of inner panels 2 with electronics equipment 2a mounted thereon, being arranged inside an artificial satellite structure 1, a loop type heat pipe 3 being connected to the inner panels 2, having an evaporator 3a, a condenser 3b, a liquid pipe 3c connecting the evaporator 3a and the condenser 3b, where vapor phase operating fluid is flowing, and a liquid pipe 3d connecting the evaporator 3a and the condenser 3b, where liquid phase operating fluid is flowing, a connecting part 8a connecting the inner panels 2 and the loop type heat pipe 3, and an expandable type radiator panel 4 being connected to the inner panel 2 via a loop type heat pipe 3, as well as being foldably and expandably supported in the artificial satellite structure.
      COPYRIGHT: (C)2004,JPO
    • 要解决的问题:提供一种用于人造卫星的热控制装置,其能够在不消耗人造卫星的任何电能的情况下进行热量控制。 解决方案:热控制装置包括安装有电子设备2a的多个内板2,布置在人造卫星结构1内部,环形热管3连接到内板2,其具有蒸发器3a 冷凝器3b,连接蒸发器3a和冷凝器3b的液体管3c,气相工作流体流动,液相工作流体流过的蒸发器3a和冷凝器3b连接的液体管3d, 连接内板2和环型热管3的部分8a,以及通过环型热管3连接到内板2的可膨胀型散热板4,并且可折叠地且可膨胀地支撑在人造卫星结构 。 版权所有(C)2004,JPO
    • 17. 发明专利
    • HEAT TRANSFER ELEMENT
    • JPH09262917A
    • 1997-10-07
    • JP7461196
    • 1996-03-28
    • MITSUBISHI ELECTRIC CORP
    • YAO AKIRA
    • B32B5/02B32B5/12F28F13/00H01L23/373
    • PROBLEM TO BE SOLVED: To reduce the heat resistance of an elastic heat transfer element and a heat absorbing element/a heat generating element by adding a carbon fiber anew to the end part of a carbon fiber in the carbon fiber direction. SOLUTION: A carbon fiber is added anew to the end part of a carbon fiber in the fiber direction. A heat generated by a heat generating element runs from the end of a carbon fiber 1 as shown by an arrow 5a, and at the same time, runs to the carbon fiber 10 of a fixed part to find its way into the carbon fiber 1. In addition, the thermal conductivity of the carbon fiber is exceedingly higher than that of an adhesive used for adhesion with a heating absorbing element/a heat generating element. Therefore, the end face of the carbon fiber 10 of the fixed part can be regarded as the heat transfer face of the carbon fiber 1. Thus it is possible to widen a heat transfer face on the end part of the carbon fiber 1 and reduce the thermal resistance of the flexible heat transfer element and the heat absorbing element/the heat generating element.