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    • 2. 发明公开
    • IN-BAND PSEUDOLITE WIRELESS POSITIONING METHOD, SYSTEM AND DEVICE
    • VERFAHREN,系统UND VORRICHTUNG ZUR DRAHTLOSEN PSEUDOLITPOSITIONIONUNG
    • EP3078981A4
    • 2017-06-21
    • EP14797248
    • 2014-05-21
    • ZTE CORP
    • CHEN SHIJUNHU LIUJUNYU GUANGHUILU HAITAO
    • G01S19/11G01S1/02
    • G01S19/11G01S1/02G01S1/024H04W64/00
    • Disclosed are an in-band pseudolite wireless positioning method, system and device, the system comprising: a base station, a pseudolite and a terminal; the base station is used to transmit identifier information to the pseudolite after correcting the transmission clock of the pseudolite, and transmit a pseudolite array and positioning correction information to a terminal; the pseudolite is used to generate a random positioning signal sequence according to the identifier information, and utilizes the positioning link having the same frequency band as the base station wireless system to transmit a positioning signal according to the transmission clock and the random positioning signal sequence; and the terminal is used to generate a random positioning signal sequence of the pseudolite according to the pseudolite array and the positioning correction information, and match the received positioning signal according to the random positioning signal sequence to obtain the arrival time of the positioning signal, and obtain through calculation the position coordinates of the terminal according to the position coordinates of the pseudolite and the arrival time.
    • 公开了一种带内伪卫星无线定位方法,系统和设备,该系统包括:基站,伪卫星和终端; 基站用于在校正伪卫星的传输时钟后向伪卫星传输标识信息,并向终端传输伪卫星阵列和定位校正信息; 所述伪卫星用于根据所述标识信息生成随机定位信号序列,并利用与所述基站无线系统具有相同频段的定位链路根据所述传输时钟和所述随机定位信号序列传输定位信号; 终端用于根据伪卫星阵列和定位校正信息生成伪卫星的随机定位信号序列,并根据随机定位信号序列匹配接收到的定位信号以获得定位信号的到达时间,以及 根据伪卫星的位置坐标和到达时间,通过计算得到终端的位置坐标。
    • 7. 发明公开
    • Calibration of plural - channel system
    • Eichung eines Systems von mehreren elektrischenKanälen。
    • EP0547274A1
    • 1993-06-23
    • EP91311808.9
    • 1991-12-19
    • HAZELTINE CORPORATION
    • Lopez, Alfred R.
    • H01Q3/26G01S1/02
    • G01S1/024H01Q3/267H03L7/081
    • In a system having plural signal-carrying channels, a phase shift is introduced between a signal in one of the channels and a reference signal for calibrating the individual channels. The reference signal is obtained by adding samples of signals in other ones of the channels. The phase shift is introduced by phase-shift apparatus responsive to a command signal directing a continuous monotonic increment of phase. The phase incrementing introduces a frequency shift (a serrodyne), which produces a beat-frequency signal for mixing a channel signal with the reference signal. The beat-frequency signal is phase locked to a modulation pattern of a command signal, whereby a measurement of phase (or delay) can be made between the two signals for calibration of each channel within the system. Separate calibrations may be made for different presumed values of system delay so as to obtain a value of system delay which causes the calibration sequence to converge to fixed values of phase shift introduced in each of the channels.
    • 在具有多个信号承载通道的系统中,在一个通道中的信号和用于校准各个通道的参考信号之间引入相移。 参考信号通过在其他通道中添加信号采样来获得。 相移由相移装置引入,响应于指示相位的连续单调递增的命令信号。 相位增量引入频率偏移(serrodyne),其产生用于将信道信号与参考信号混合的拍频信号。 拍频信号被锁相到命令信号的调制模式,由此可以在两个信号之间进行相位(或延迟)的测量,以校准系统内的每个通道。 可以针对系统延迟的不同推定值进行单独的校准,以便获得使得校准序列收敛到在每个通道中引入的相移的固定值的系统延迟的值。
    • 8. 发明公开
    • Improvements in or relating to aircraft landing systems
    • VerbesserungenfürFlugzeug-Landesysteme。
    • EP0516265A1
    • 1992-12-02
    • EP92301906.1
    • 1992-03-05
    • Siemens Plessey Electronic Systems Limited
    • Smart, Peter BrittonSpencer, Timothy JamesSole, John DavidBarton, Peter WilliamPeckham, RichardGraham, William MorrisWhitehurst, Jonathan
    • G01S1/56G01S1/02
    • G01S1/56G01S1/024
    • An aircraft landing system (10) is disclosed which produces electromagnetic guidance signals to an incoming aircraft (14) and which allow the incoming aircraft (14) to safely land upon the runway (16). This system (10) includes various antenna arrays (12, 18), and (20) which are orientated so as to provide signals in several directions. Each of these arrays has a separate controller (22, 24), and (26) having a separate transmitter controller (74) uniquely coupled to each of the antennas (80, 88). Each of the transmitter controllers (74) separately amplifies the incoming electromagnetic energy from transmitters (52, 54). System 10 further includes several fault monitors (92, 94, 96) which monitor the operation of system (10) and which further provide self test features. System (10) further includes voting circuitry (98, 118) to allow for continued system operation even upon the failure of one or more of the transmitter controllers (74) and/or the monitors (92, 94, 96) and a dual inclined travelling wave manifold (90) and (566) to provide a monitored beam output which is used by monitors (92, 94, 96) to ensure continued system operation. Further, system 10 includes a connectorless coupling of electromagnetic energy between each of the transmitter controllers (74) and the combiners (82, 84). This connectorless coupling allows for a more efficient energy transfer while obviating the need for separate physical connections which are inherently unreliable; inefficient; and costly.
    • 公开了一种飞机着陆系统(10),其向进入的飞行器(14)产生电磁引导信号,并允许进入的飞机(14)安全地着陆在跑道(16)上。 该系统(10)包括各种天线阵列(12,18)和(20),其被定向成在多个方向上提供信号。 这些阵列中的每一个具有单独的控制器(22,24)和(26),其具有唯一地耦合到每个天线(80,88)的单独的发射器控制器(74)。 每个发射机控制器(74)分别放大来自发射器(52,54)的输入电磁能量。 系统10还包括几个故障监视器(92,94,96),其监视系统(10)的操作并进一步提供自检特征。 系统(10)还包括投票电路(98,118),以允许即使在一个或多个发射器控制器(74)和/或监视器(92,94,96)的故障和连续的系统操作 行波管道(90)和(566),以提供由监视器(92,94,96)使用的监视的光束输出,以确保持续的系统操作。 此外,系统10包括在每个发射机控制器(74)和组合器(82,84)之间的无连接器的电磁能耦合。 这种无连接器耦合允许更有效的能量传递,同时避免对本来不可靠的单独的物理连接的需要; 效率低下; 并且成本高昂。