Kalman filtering techniques are combined with a semianalytical orbit generator to develop a sequential orbit determination algorithm. The algorithm is investigated for computational efficiency, accuracy, and radius of convergence by comparison with truth ephemerides and a Cowell special perturbations filters (GTDS). Test cases relevant to satellite navigation are examined.
Semiannalytical satellite theory and sequential estimation
01.10.1980
Aufsatz (Konferenz)
Keine Angabe
Englisch
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