利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

10 条记录 (耗时 0.012 秒)

    Pressure tight large-scaled membrane structure
    1.
    发明公开
    Pressure tight large-scaled membrane structure 审中-公开
    紧压大型膜结构

    公开(公告)号：EP2145821A2

    公开(公告)日：2010-01-20

    申请号：EP09009101.8

    申请日：2009-07-13

    申请人： The Japan Aerospace Exploration Agency ,  Fujikura Parachute Company, Ltd.

    发明人： Izutsu, Naoki ,  Matsushima, Kiyoho

    IPC分类号： B64B1/44 ,  B64B1/58

    CPC分类号： B64B1/44 ,  B64B1/58 ,  B64B1/70

    摘要： A pressure tight large-scaled membrane structure comprising a bag body(2) having a plurality of gores(3) attached to each other along an attachment line, and a plurality of first ropes(7) attached over a predetermined range of the bag body(2) in such a manner as to be orthogonal to the attachment line of the gores(3), whereby a cylindrical shaped portion(6) is formed. The cylindrical shaped portion(6) has a substantially circular cross-sectional area that is a maximum substantially circular cross-section of the bag body(2) and the plurality of first ropes(7) each having approximately the same length as a circumference of the substantially circular-cross section having a maximum area with respect to the bag body(2).

    摘要翻译： 一种耐压大型膜结构，其特征在于，包括：袋体（2），其具有沿着连结线彼此连接的多个穴（3）;以及多个第一绳索（7），所述多个第一绳索（7） （2）以与孔（3）的连接线正交的方式形成圆柱形部分（6）。 圆柱形部分（6）具有基本上圆形的横截面区域，该横截面区域是袋体（2）和多个第一绳索（7）的最大基本圆形的横截面，每个第一绳索具有与 该大致圆形横截面相对于袋体（2）具有最大面积。

    ANTENNA AND MANUFACTURING METHOD THEREFOR
    3.
    发明公开
    ANTENNA AND MANUFACTURING METHOD THEREFOR 审中-公开
    天文台在赫尔辛基

    公开(公告)号：EP2378608A1

    公开(公告)日：2011-10-19

    申请号：EP09833466.7

    申请日：2009-12-10

    申请人： NEC TOSHIBA Space Systems, Ltd. ,  The Japan Aerospace Exploration Agency

    发明人： AMANO, Osamu ,  KOREEDA, Shuichi ,  KAMATA, Yukio ,  ANDO, Makoto

    IPC分类号： H01Q1/38 ,  H01Q21/06

    CPC分类号： H01Q21/064 ,  H01Q1/288 ,  H01Q1/38 ,  Y10T29/49016

    摘要： Provided is an antenna capable of establishing electrical conductivity between a flange-like short-circuit section, of a power supply section and a thin metal plate (for example, copper foil) even in a harsh temperature environment in a space environment. Under a state in which an apical portion (31) of a power supply section (30) is inserted from an outer side of a face plate (20) into a hole (50) for the power supply section of a thin metal plate (copper foil) (21), a dielectric plate (22), and a metal plate (ring-like metal plate) (40), a plurality of screws (60) are inserted from the outer side of a flange-like short-circuit section (32) through a plurality of insertion holes (65) of the flange-like short-circuit section, (32), the thin metal plate (copper foil) (21), and the dielectric plate (22), and the plurality of screws (60) are threadingly inserted into a plurality of tapped holes (70) of the metal plate (ring-like metal plate) (40) so that electrical conductivity between the flange-like short-circuit section (32) and the thin metal plate (copper foil) (21) is established through direct contact.

    摘要翻译： 提供一种能够在空间环境中的恶劣的温度环境下，在电源部的法兰状的短路部和薄金属板（例如铜箔）之间建立导电性的天线。 在电源部（30）的顶端部（31）从面板（20）的外侧插入用于薄金属板（铜箔）的供电部的孔（50）的状态下， 箔）（21），电介质板（22）和金属板（环状金属板）（40），多个螺钉（60）从法兰状短路部分的外侧插入 （32），所述薄板状金属板（铜箔）（21）和所述电介质板（22）通过所述凸缘状短路部（32）的多个插入孔（65），所述多个 螺钉（60）螺纹地插入金属板（环状金属板）（40）的多个螺纹孔（70）中，使得凸缘状短路部（32）和薄金属 通过直接接触建立板（铜箔）（21）。

    High bypass-ratio turbofan jet engine
    5.
    发明公开
    High bypass-ratio turbofan jet engine 有权
    Turbofan-Strahlmotor mit hohemNebenstromverhältnis

    公开(公告)号：EP2098714A2

    公开(公告)日：2009-09-09

    申请号：EP09153344.8

    申请日：2009-02-20

    申请人： The Japan Aerospace Exploration Agency

    发明人： YanagiI, Ryoji ,  Fujiwara, Hitoshi

    IPC分类号： F02K3/065

    CPC分类号： F02K3/065 ,  B64C7/02 ,  B64D29/02 ,  F02C7/04 ,  F05D2250/14 ,  Y02T50/671

    摘要： A turbofan jet engine (100) is provided which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct (20) that discharges air compressed by a front fan (10) to the atmosphere and an aft fan duct (50) that introduces air into an aft fan (40) are disposed such as to change cross-sectional shapes thereof by rotating around a core engine (30) in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted.

    摘要翻译： 提供一种涡轮风扇喷气发动机（100），其能够增加旁路比，而不增加风扇直径，并且降低作用在发动机上的空气阻力;前风扇导管（20），其排出由前风扇（10 ）和将空气引入后风扇（40）的后风扇导管（50）设置成通过围绕芯发动机（30）沿逆时针方向旋转来改变其横截面形状，使得 在前风扇之前的位置处的前风扇风道和后风扇管道之间的横截面几何关系以及在前风扇管道和后风扇管道之间在紧邻前风扇前方的位置之间的横截面几何关系 被倒置

    Pressure tight large-scaled membrane structure
    8.
    发明公开
    Pressure tight large-scaled membrane structure 审中-公开
    Druckdichte，großformatigeMembranstruktur

    公开(公告)号：EP2145821A3

    公开(公告)日：2010-10-06

    申请号：EP09009101.8

    申请日：2009-07-13

    申请人： The Japan Aerospace Exploration Agency ,  Fujikura Parachute Company, Ltd.

    发明人： Izutsu, Naoki ,  Matsushima, Kiyoho

    IPC分类号： B64B1/44 ,  B64B1/58

    CPC分类号： B64B1/44 ,  B64B1/58 ,  B64B1/70

    摘要： A pressure tight large-scaled membrane structure comprising a bag body(2) having a plurality of gores(3) attached to each other along an attachment line, and a plurality of first ropes(7) attached over a predetermined range of the bag body(2) in such a manner as to be orthogonal to the attachment line of the gores(3), whereby a cylindrical shaped portion(6) is formed. The cylindrical shaped portion(6) has a substantially circular cross-sectional area that is a maximum substantially circular cross-section of the bag body(2) and the plurality of first ropes(7) each having approximately the same length as a circumference of the substantially circular-cross section having a maximum area with respect to the bag body(2).

    摘要翻译： 一种压力紧密的大型膜结构，包括具有沿着连接线彼此附接的多个孔（3）的袋体（2）和多个第一绳索（7），所述第一绳索（7）附接在所述袋体的预定范围 （2）以与所述山灰（3）的安装线正交的方式形成圆筒形部分（6）。 圆柱形部分（6）具有基本上圆形的横截面面积，其是袋体（2）的最大基本圆形横截面，并且多个第一绳索（7）各自具有与圆周 所述大致圆形横截面相对于所述袋体（2）具有最大面积。

    ULTRASONIC TEST METHOD AND ULTRASONIC TEST INSTRUMENT USED FOR SAME
    9.
    发明公开
    ULTRASONIC TEST METHOD AND ULTRASONIC TEST INSTRUMENT USED FOR SAME 有权
    ULTRASCHALLTESTVERFAHREN UNDDAFÜRVERWENDETESULTRASCHALLTESTGERÄT

    公开(公告)号：EP1821099A1

    公开(公告)日：2007-08-22

    申请号：EP05806260.5

    申请日：2005-11-11

    申请人： Independent Administrative Institution, The Japan Aerospace Exploration Agency

    发明人： SHIRAI, Makoto, Ind. admin. Inst. Japan Aerospace ,  MIYAMOTO, H., Ind. admin. Inst. Japan Aerospace ,  MATSUBARA, S. Non-Destructive Insp. CompanyLtd.

    IPC分类号： G01N29/24

    CPC分类号： G01N29/043 ,  G01N29/07 ,  G01N29/223 ,  G01N29/32 ,  G01N29/38 ,  G01N2291/0231 ,  G01N2291/0427 ,  G01N2291/044 ,  G01N2291/056 ,  G01N2291/102 ,  G01N2291/2694

    摘要： An ultrasonic test method for detecting a defective portion more precisely in a noncontact reflection way, and ultra-sonic test instrument used for the method. An ultrasonic wave is transmitted from a transmitter (20 (21)) provided on one side of an object under test, and the reflected wave is received by a receiver (30 (31)) provided on the same side. The ultrasonic wave is transmitted/received through an air layer between the transmitter and the object (100) under test and between the receiver and the object (100). The relative positions of the transmitter (20), the receiver (30), and the object (100) are so determined that the air propagation time ta of the air path (RA) between the transmitter and the receiver is longer than the propagation time tb of the reflected wave in the reflection path (RB). The propagation of the ultrasonic wave through the solid body between the transmitter and the receiver is blocked. This invention is suitable to test laminated material (100) such as a laminate of CFRP (101) and insulation (102) in a noncontact way.

    摘要翻译： 一种用于以非接触反射方式更准确地检测缺陷部分的超声波测试方法，以及用于该方法的超声波测试仪器。 从设置在被测物体的一侧的发送器（20（21））发送超声波，反射波由设置在同一侧的接收器（30（31））接收。 超声波通过发射机与待测物体（100）之间的空气层和接收器与物体（100）之间的空气层进行传输/接收。 如此确定发射器（20），接收器（30）和物体（100）的相对位置，使得发射器和接收器之间的空气路径（RA）的空气传播时间ta比传播时间长 在反射路径（RB）中的反射波的tb。 超声波在发射机和接收机之间通过固体的传播被阻断。 本发明适用于以非接触方式测试诸如CFRP（101）和绝缘体（102）的层压材料的层合材料（100）。

    High bypass-ratio turbofan jet engine
    10.
    发明公开
    High bypass-ratio turbofan jet engine 有权
    高分流比涡扇喷气发动机

    公开(公告)号：EP2098714A3

    公开(公告)日：2010-07-07

    申请号：EP09153344.8

    申请日：2009-02-20

    申请人： The Japan Aerospace Exploration Agency

    发明人： YanagiI, Ryoji ,  Fujiwara, Hitoshi

    IPC分类号： F02K3/065 ,  F02C7/04

    CPC分类号： F02K3/065 ,  B64C7/02 ,  B64D29/02 ,  F02C7/04 ,  F05D2250/14 ,  Y02T50/671

    摘要： A turbofan jet engine (100) is provided which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct (20) that discharges air compressed by a front fan (10) to the atmosphere and an aft fan duct (50) that introduces air into an aft fan (40) are disposed such as to change cross-sectional shapes thereof by rotating around a core engine (30) in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted.