Physics
Scientific paper
Oct 1985
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1985cemec..37..149t&link_type=abstract
Celestial Mechanics (ISSN 0008-8714), vol. 37, Oct. 1985, p. 149-159.
Physics
4
Orbit Calculation, Orbital Elements, Satellite Orbits, Position Errors, Steepest Descent Method
Scientific paper
A robust analytical formulation is developed to apply classical initial orbital determination to artificial satellites whose locations are uncertain to about 1 cu km and separated in time by no more than 30 min. An analytical simplification reduces Gauss's method, iteration on the semilatus rectum, iteration on the true anomaly, and the Lambert-Euler technique, to the solution of a single equation in one unknown, instead of the usual coupled triplet of three equations in three unknowns. The method is demonstrated for all common artificial satellite orbits over a variety of time intervals between the two location vectors, and for a varied set of position and distance errors.
Randall M. S. P.
Taff Laurence G.
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