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    SYSTEM AND METHOD FOR GENERATING A PHASE SCINTILLATION MAP UTILIZED FOR DE-WEIGHTING OBSERVATIONS FROM GNSS SATELLITES
    15.
    发明申请
    SYSTEM AND METHOD FOR GENERATING A PHASE SCINTILLATION MAP UTILIZED FOR DE-WEIGHTING OBSERVATIONS FROM GNSS SATELLITES 审中-公开

    公开(公告)号：US20190056505A1

    公开(公告)日：2019-02-21

    申请号：US15679758

    申请日：2017-08-17

    申请人： NovAtel Inc.

    发明人： Thomas Morley

    IPC分类号： G01S19/04 ,  G01S19/43 ,  G01S19/07 ,  G01S19/05 ,  G01S19/08

    CPC分类号： G01S19/08 ,  G01S19/05 ,  G01S19/07 ,  G01S19/28 ,  G01S19/43

    摘要： A system and method generates a phase scintillation map that is utilized to de-weight satellite signal observations from GNSS satellites. One or more base stations each assign an index value to one or more GNSS satellite in view, where the index value indicates an adverse effect of ionospheric scintillation on signals received from the GNSS satellite. The values and identifiers may be transmitted to a server. The server utilizes the received information to generate the phase scintillation map that may include one or more scintillation bubbles, wherein a location of each scintillation bubble is based on the received information. The phase scintillation map is transmitted to one or more rovers. The rover determines if a pierce point associated with a selected GNSS satellite in view of the rover falls within the boundaries of a scintillation bubble. If so, satellite signal observations from the selected GNSS satellite are de-weighted.

    SYSTEM FRAMEWORK FOR MOBILE DEVICE LOCATION
    17.
    发明申请
    SYSTEM FRAMEWORK FOR MOBILE DEVICE LOCATION 审中-公开

    公开(公告)号：US20180210063A1

    公开(公告)日：2018-07-26

    申请号：US15933262

    申请日：2018-03-22

    申请人： ETHERWHERE CORPORATION

    发明人： Farrokh Farrokhi

    IPC分类号： G01S5/02 ,  G01S19/42 ,  G01S19/05

    CPC分类号： G01S5/0252 ,  G01S19/05 ,  G01S19/42

    摘要： A system for measuring the pseudo range from a target GPS sensor to a designated navigational satellite, for use in a satellite positioning system (SPS) is comprised of multiple GPS sensors for receiving and recording portions of the signals transmitted by designated navigational satellites, the recordings referred to as datagrams; and means for transmitting the datagrams to a datagram processing facility wherein the pseudo range from the target GPS sensor to the designated navigational satellite is derived. The datagram processing facility for deriving the pseudo range is further comprised of a pseudo range engine for deriving a pseudo range from a datagram originating with said target GPS sensor, the location of which is to be determined, the derivation accomplished with the aid of a perfect reference; a perfect reference engine for generating a perfect reference from one or more satellite-specific datagrams: and a strong signal suppression engine for synthesizing satellite-specific datagrams from I/F signals recorded by reference GPS sensors designated for the express purpose of perfect reference generation. The perfect reference reduces the minimum signal strength required to acquire and accurately track GPS satellites at or near the horizon.

    Method and device for determining availability of ARAIM system
    18.
    发明授权
    Method and device for determining availability of ARAIM system 有权

    公开(公告)号：US09958551B1

    公开(公告)日：2018-05-01

    申请号：US15723543

    申请日：2017-10-03

    申请人： Beihang University

    发明人： Zhipeng Wang ,  Yanbo Zhu ,  Wei Shao ,  Qiang Li

    IPC分类号： G01S19/42 ,  G01S19/25 ,  G01S19/05 ,  G01S19/41 ,  G01S19/00

    CPC分类号： G01S19/42 ,  G01S19/05 ,  G01S19/15 ,  G01S19/20 ,  G01S19/256 ,  G01S19/41

    摘要： A method for evaluating the availability of ARAIM system is provided. A satellite position coordinate and clock offset of each satellite at a current time point and several time points before the current time point are received. Empirical mode decomposition is performed on the position coordinate and the clock offset respectively, to obtain a position coordinate mode component and a clock offset mode component of each satellite at each time point. A position coordinate mode component and a clock offset mode component of each satellite at a time point next to the current time point are obtained respectively. According to the position coordinate mode component and the clock offset mode component of each satellite at the time point next to the current time point, a position coordinate mode component and a clock offset mode component of each satellite at a next time point is obtained, thereby obtaining an evaluation result.