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    • 3. 发明授权
    • Energy transmission arrangement
    • 能量传输安排
    • US5400036A
    • 1995-03-21
    • US128286
    • 1993-09-29
    • Jiro KochiyamaNobuyuki KayaTeruo FujiwaraHidemi YasuiHiroyuki Yashiro
    • Jiro KochiyamaNobuyuki KayaTeruo FujiwaraHidemi YasuiHiroyuki Yashiro
    • H02J17/00H01Q1/24H01Q3/26H04B1/04H04B1/18H04B7/185H01Q1/00
    • H04B7/185H01Q1/248H01Q3/2629
    • 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.
    • 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。
    • 4. 发明授权
    • Ranging method using telemetering and apparatus employing said method
    • 使用电话的方法和使用方法的装置的方法
    • US5194869A
    • 1993-03-16
    • US916943
    • 1992-07-20
    • Jiro KochiyamaMakoto MiwadaToshiaki SatoTakuji MoritaTeruo FujiwaraShoji KanedaKazutaka MarutaHajime Ogawa
    • Jiro KochiyamaMakoto MiwadaToshiaki SatoTakuji MoritaTeruo FujiwaraShoji KanedaKazutaka MarutaHajime Ogawa
    • B64G3/00F41G3/00G01S11/02G01S11/08G08C17/02
    • G01S11/08G08C17/02
    • 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.
    • 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。
    • 6. 发明授权
    • Rocket attitude control apparatus
    • 火箭姿态控制装置
    • US4384694A
    • 1983-05-24
    • US171466
    • 1980-07-23
    • Yasushi WatanabeTeruo FujiwaraKunio Shimano
    • Yasushi WatanabeTeruo FujiwaraKunio Shimano
    • B64D33/04B64G1/00F02K9/80F02K9/82F02K9/90F42B15/18
    • F02K9/82F02K9/805F02K9/90
    • 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.
    • 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。