The problem of the satellite's orbit refinement from the ground range measurements is revisited.The theoretical background of the measurements modeling is described. Two approaches to theorbit refinement, namely, differential correction of the initial orbit by the least squares batchmeasurement processing, and the sequential estimation of the current satellite's state vector bythe extended Kalman filter are set forth, as applied to the EROS-A1 radar range data. Theobtained results are shown, which display the fits of the modeled ranges to the measurements tokeep within 10 meters in the absence of the short-term biases. Some considerations concerningthe prediction properties of the refined orbit are stated.
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