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Post-flight differential correction analysis using Vinti's spheroidal method for the small astronomy satellite orbitThe results of an intensive analysis of a differential orbit improvement method utilizing observational data for a 550-kilometer altitude, near-circular, near-equatorial satellite orbit are presented. Observations of the Small Astronomy Satellite (SAS-1) are in the form of direction cosines as measured at two ground interferometer tracking stations near the Equator during the first 22 orbital revolutions (approximately 37 hours) after launch of the spacecraft. Numerical results, in both tabular and graphical form, are displayed for numerous iterated fittings of various observational arcs by differential correction of the orbital elements. Parameters varied in these comparative cases include the time duration of the observational data block, the number of pairs of direction cosine data and the number of tracking station passes included in the solution, the distribution of such passes between the two available tracking stations, and the acceptance criterion for the observational residuals in the least squares fitting procedure. It was found that three observational pairs of direction cosine data, the minimum number possible for a uniquely determined solution in theory, are sufficient to promote covergence to an accurate solution, if properly selected.
Document ID
19740024147
Acquisition Source
Legacy CDMS
Document Type
Preprint (Draft being sent to journal)
Authors
Walden, H. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
Space Sciences
Report/Patent Number
NASA-TM-X-70720
X-582-74-207
Accession Number
74N32260
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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