A sequential navigation algorithm for a navigator using the Global Positioning System satellites is developed and tested for both noise-free and noisy system models. Data from a six-hour flight from California to Hawaii (C5A aircraft) simulates a true user to test the accuracy of the user's position for a sequential navigation system. For error reduction in the user's position in the sequential navigation system (considering 100 m as a maximum average error tolerated by any low-cost GPS user) an analysis of error sources in the sequential system has led to the use of range-ephemeris rate to translate ranges to a common point in time and to use velocity aiding at the time of a satellite disappearance. To reduce the user's position and velocity errors in a noisy navigation system an 'alpha-beta' two-pole filter is implemented whose optimum alpha is obtained experimentally. A user's position error of 73 m at noise range error of 30.48 (1sigma) is achieved.


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    Title :

    A navigation algorithm for single channel low-cost GPS receiver


    Contributors:
    Parsiani, H. (author) / Noe, P. S. (author) / Rhyne, V. T. (author) / Painter, J. H. (author)

    Conference:

    In: Challenge of the ''80s; Proceedings of the Third Digital Avionics Systems Conference ; 1979 ; Fort Worth, TX


    Publication date :

    1979-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





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