Use of GNSS‐Based Pseudo‐Acceleration Measurements and Orbital Constraints to Initialize Spaceborne Receiver Orbit Solutions

This paper presents an original technique based on pseudo‐acceleration measurements to compute a fix with a global navigation satellite system (GNSS) spaceborne receiver. The pseudo‐acceleration measurements can be computed by pseudorange differencing, and the relation between the position and the a...

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Bibliographic Details
Published in:Navigation (Washington) 2003-06, Vol.50 (2), p.95-101
Main Authors: LAURICHESSE, D., GRATTON, S., MERCIER, F., TOURNIER, T., BERTHIAS, J. P., ISSLER, J. L., DOLISZNY, F., REVIDON, P.
Format: Article
Language:English
Subjects:
Applied sciences
Exact sciences and technology
Radiolocalization and radionavigation
Sciences of the Universe
Telecommunications
Telecommunications and information theory
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Summary:This paper presents an original technique based on pseudo‐acceleration measurements to compute a fix with a global navigation satellite system (GNSS) spaceborne receiver. The pseudo‐acceleration measurements can be computed by pseudorange differencing, and the relation between the position and the acceleration is given by Newton's law. Then, a least‐squares system resolution makes it possible to obtain the state of the receiver (position, velocity, clock bias, and drift) when only two emitters are visible in a low earth orbit (LEO) configuration, and when these data are adapted to geostationary earth orbit (GEO) orbits, one can obtain the state of the receiver when only one GNSS emitter is visible.
ISSN:0028-1522
2161-4296
DOI:10.1002/j.2161-4296.2003.tb00321.x