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A navigation algorithm for single channel low-cost GPS receiverA 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.
Document ID
19800048287
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Parsiani, H.
(Intermetrics, Inc. Pearland, Tex., United States)
Noe, P. S.
(Texas A&M Univ. College Station, TX, United States)
Rhyne, V. T.
(Texas A&M Univ. College Station, TX, United States)
Painter, J. H.
(Texas A & M University College Station, Tex., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1979
Subject Category
Aircraft Communications And Navigation
Meeting Information
Meeting: In: Challenge of the ''80s; Proceedings of the Third Digital Avionics Systems Conference
Location: Fort Worth, TX
Start Date: November 6, 1979
End Date: November 8, 1979
Accession Number
80A32457
Funding Number(s)
CONTRACT_GRANT: NSG-1374
Distribution Limits
Public
Copyright
Other

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