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Semiannalytical satellite theory and sequential estimationKalman 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.
Document ID
19810002566
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Taylor, S. P. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Cefola, P. J. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Date Acquired
August 11, 2013
Publication Date
October 1, 1980
Publication Information
Publication: NASA. Goddard Space Flight Center Fifth Ann. Flight Mech.(Estimation Theory Symp.
Subject Category
Astrodynamics
Accession Number
81N11074
Funding Number(s)
CONTRACT_GRANT: F04701-79-C-0062
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19810002562Collected WorksFifth Annual Flight Mechanics/Estimation Theory Symposium
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