Computer Science
Scientific paper
Oct 1976
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1976stin...7726047p&link_type=abstract
Unknown
Computer Science
Artificial Satellites, Orbit Calculation, Orbital Elements, Bearing (Direction), Doppler Effect, Earth Orbits, Eccentricity, Ground Stations, Iterative Solution, Kepler Laws, Orbit Perturbation, Position (Location), Rangefinding
Scientific paper
A procedure to determine mean orbital elements of earth satellites from two topocentric position vectors plus Doppler measurements is described. This procedure is iterative and generally starts with the Kepler approximation. Doppler measurements limit the number of quantities to be iteratively corrected to two. This method utilizes the fact that the energy and a rotation impulse component represent motion constants (and are, naturally, functions of the mean orbital elements). In the case of orbits of smaller eccentricity, classical orbital elements are replaced by orbital parameters which do not have singularities. The perturbations, according to the Brouwer theory, are transformed for these orbital parameters.
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