利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

13 条记录 (耗时 0.026 秒)

    Transparent conductive film and method of making the film
    1.
    发明授权
    Transparent conductive film and method of making the film 失效
    透明导电膜及其制作方法

    公开(公告)号：US06329044B1

    公开(公告)日：2001-12-11

    申请号：US09344803

    申请日：1999-06-25

    申请人： Katsumi Inoue ,  Yasuhiko Akao ,  Satoru Takaki ,  Yasuo Hayashi ,  Teruo Fujiwara

    发明人： Katsumi Inoue ,  Yasuhiko Akao ,  Satoru Takaki ,  Yasuo Hayashi ,  Teruo Fujiwara

    IPC分类号： B32B900

    CPC分类号： C23C14/086 ,  B32B17/10174 ,  C03C17/253 ,  C03C2217/231 ,  C03C2217/24 ,  C03C2218/15 ,  C03C2218/152 ,  C03C2218/154 ,  H01B1/08 ,  Y10T428/24917

    摘要： Transparent conductive films are provided which provide high sheet resistance, high transparency, high heat resistance and high moisture resistance, wherein the transparent conductive films contain either (a) an oxide film made of a mixed oxide of indium and tin and doped with at least 0.01 and less than 0.6 weight % of nitrogen and a geometrical thickness of from 5 to 25 nm or (b) an oxide film made of a mixed oxide of indium and tin, wherein the oxide film contains tin within a range of from 4.2 to 8.3 atomic % based on indium and a geometrical thickness of from 5 to 20 nm, and where in each case (a) and (b) the oxide film has a light transmittance of more than 90% at a wavelength of 550 nm, transparent conductive film-coated substrates prepared therefrom and touch panels prepared from the transparent conductive film-coated substrates.

    摘要翻译： 提供透明导电膜，其提供高的薄层电阻，高透明度，高耐热性和高耐湿性，其中透明导电膜包含（a）由铟和锡的混合氧化物制成的氧化物膜，并掺杂至少0.01 和小于0.6重量％的氮，几何厚度为5至25nm，或（b）由铟和锡的混合氧化物制成的氧化物膜，其中所述氧化物膜含有锡在4.2至8.3原子的范围内 基于铟的几何厚度为5〜20nm的几何厚度，并且在（a）和（b）的每种情况下，氧化物膜在波长550nm下的透光率大于90％，透明导电膜 - 由其制备的涂覆基材和由透明导电膜涂覆的基材制备的触摸面板。

    Energy transmission arrangement
    6.
    发明授权
    Energy transmission arrangement 失效
    能量传输安排

    公开(公告)号：US5400036A

    公开(公告)日：1995-03-21

    申请号：US128286

    申请日：1993-09-29

    申请人： Jiro Kochiyama ,  Nobuyuki Kaya ,  Teruo Fujiwara ,  Hidemi Yasui ,  Hiroyuki Yashiro

    发明人： Jiro Kochiyama ,  Nobuyuki Kaya ,  Teruo Fujiwara ,  Hidemi Yasui ,  Hiroyuki Yashiro

    IPC分类号： H02J17/00 ,  H01Q1/24 ,  H01Q3/26 ,  H04B1/04 ,  H04B1/18 ,  H04B7/185 ,  H01Q1/00

    CPC分类号： H04B7/185 ,  H01Q1/248 ,  H01Q3/2629

    摘要： An energy transmission arrangement emits a microwave energy signal to a target location on the basis of a pilot signal received from the target location. The arrangement includes a plurality of pilot antennas for receiving the pilot signal and a plurality of antenna elements for transmission of the energy signal. The pilot signal as received at a first pilot antenna is multiplied at a phase conjugation circuit and divided into a plurality of transmission signals corresponding to the plurality of antenna elements. A target direction is calculated based on a phase difference of the pilot signal as received at each of the other pilot antennas and a phase adjustment circuit is provided for adjusting the phases of each of the transmission signals on the basis of the calculated target direction. Electrical energy is then supplied from energy collecting means to a plurality of amplifiers and amplified respectively, on the basis of a corresponding one of the transmission signals, to be supplied to respective antenna elements to be emitted as the microwave energy signal. According to this arrangment, the phase conjugation circuit is active to receive the pilot signal as received at the first pilot antenna as well as the pilot signal as received at a predetermined reference point in the path of the pilot signal for calculating a difference signal for effecting phase correction of the microwave energy signal.

    摘要翻译： 能量传输装置基于从目标位置接收到的导频信号向目标位置发射微波能量信号。 该装置包括用于接收导频信号的多个导频天线和用于传输能量信号的多个天线元件。 在第一导频天线处接收到的导频信号在相位共轭电路处相乘，并被分成与多个天线元件对应的多个传输信号。 基于在每个其他导频天线处接收的导频信号的相位差来计算目标方向，并且提供相位调整电路，用于根据计算的目标方向来调整每个发送信号的相位。 然后将电能从能量收集装置提供给多个放大器，并且基于相应的一个传输信号分别放大，以提供给作为微波能量信号发射的各个天线元件。 根据这种布置，相位共轭电路有效地接收在第一导频天线处接收到的导频信号以及在导频信号的路径中的预定参考点处接收的导频信号，用于计算用于实现的差分信号 微波能量信号的相位校正。

    Ranging method using telemetering and apparatus employing said method
    7.
    发明授权
    Ranging method using telemetering and apparatus employing said method 失效
    使用电话的方法和使用方法的装置的方法

    公开(公告)号：US5194869A

    公开(公告)日：1993-03-16

    申请号：US916943

    申请日：1992-07-20

    申请人： Jiro Kochiyama ,  Makoto Miwada ,  Toshiaki Sato ,  Takuji Morita ,  Teruo Fujiwara ,  Shoji Kaneda ,  Kazutaka Maruta ,  Hajime Ogawa

    发明人： Jiro Kochiyama ,  Makoto Miwada ,  Toshiaki Sato ,  Takuji Morita ,  Teruo Fujiwara ,  Shoji Kaneda ,  Kazutaka Maruta ,  Hajime Ogawa

    IPC分类号： B64G3/00 ,  F41G3/00 ,  G01S11/02 ,  G01S11/08 ,  G08C17/02

    CPC分类号： G01S11/08 ,  G08C17/02

    摘要： A ranging method for measuring the flight distance of a flight object is implemented by means of a simple system construction. The ranging method is also capable of continuing ranging even if an interruption occurs in data transmission. The ranging method comprises the steps of inserting ranging pulses in a telemeter signal transmitted from a transmitting apparatus provided on the flight object, separating and extracting a ranging pulse from a telemeter signal received by a receiving apparatus provided on the ground side, obtaining a time difference between the ranging pulse and a reference clock signal generated in the receiving apparatus on the basis of a time reference equal to that of the transmitting apparatus (clock signal periods t1 and t2 of both time references are equal), and calculating the flight distance. Since there is no need to provide a transponder or the like on the flight object nor to provide a ranging-tracking system on the ground side, it is possible to realize a simple system construction. Since the ranging pulses are transmitted in the state of being contained in the telemeter signal, it is not necessary to independently prepare ranging-signal transmiting means. In addition, since the telemeter signal can be restored at any time on the ground side, it is possible to prevent ranging from being made impossible due to the interruption of transmission of the signal.

    摘要翻译： 用于测量飞行物体的飞行距离的测距方法是通过简单的系统结构实现的。 即使在数据传输中发生中断，测距方法也能够继续测距。 测距方法包括以下步骤：将测距脉冲插入到从设置在飞行对象上的发射装置发送的遥测仪信号中，从设置在地面侧的接收装置接收的遥测仪信号中分离并提取测距脉冲，获得时差 基于等于发送装置的时间基准（两个时间基准的时钟信号周期t1和t2相等），在接收装置中产生的测距脉冲和参考时钟信号之间，并计算飞行距离。 由于不需要在飞行对象上提供应答器等，也不需要在地面侧设置测距跟踪系统，因此可以实现简单的系统构造。 由于测距脉冲以包含在遥测信号中的状态发送，所以不需要独立地准备测距信号发送装置。 此外，由于可以在地面侧的任何时间恢复遥测信号，所以可以防止由于信号的发送中断而不能进行测距。

    Rocket attitude control apparatus
    9.
    发明授权
    Rocket attitude control apparatus 失效
    火箭姿态控制装置

    公开(公告)号：US4384694A

    公开(公告)日：1983-05-24

    申请号：US171466

    申请日：1980-07-23

    申请人： Yasushi Watanabe ,  Teruo Fujiwara ,  Kunio Shimano

    发明人： Yasushi Watanabe ,  Teruo Fujiwara ,  Kunio Shimano

    IPC分类号： B64D33/04 ,  B64G1/00 ,  F02K9/80 ,  F02K9/82 ,  F02K9/90 ,  F42B15/18

    CPC分类号： F02K9/82 ,  F02K9/805 ,  F02K9/90

    摘要： For controlling the attitude of a rocket including a rocket fuselage and a thrust nozzle integrally attached to the rear end of the rocket fuselage and having a nozzle throat located longitudinally intermediate thereof, a rocket attitude control apparatus comprises a plurality of thrust vector control units disposed at the outer periphery of the thrust nozzle between the nozzle throat and the rear end of the thrust nozzle in circumferentially equiangularly spaced relationship to each other, and each including a fluid injecting nozzle projectable and retractable into and out of the thrust nozzle and having an injecting bore therein, wherein said fluid injecting nozzle is permitted to project into the thrust nozzle while being cooled by fluid injected from the injecting bore into the thrust nozzle. The projection of the fluid injecting nozzle causes a stream of combustion gas passing through the thrust nozzle to be partially disturbed for controlling the attitude of the rocket.

    摘要翻译： 为了控制包括火箭机身和一体地附接到火箭机身后端的推力喷嘴的火箭的姿态，并且具有位于其纵向中间的喷嘴喉部，火箭姿态控制装置包括多个推力矢量控制单元 喷嘴喉部和推力喷嘴的后端之间的推力喷嘴的外周彼此沿周向等角度间隔开的关系，并且每个包括流体喷射喷嘴，该喷嘴可以伸出并伸出到推力喷嘴中并具有喷射孔 其中允许所述流体喷射喷嘴在被从喷射孔注入到推力喷嘴中的流体冷却时突出到推力喷嘴中。 流体喷射喷嘴的突起使得通过推力喷嘴的燃烧气体流部分地受到干扰，以控制火箭的姿态。