Semi-analytical procedure for the propagation of artificial satellite orbits based on parameter estimation

A procedure to propagate the orbit of terrestrial artificial satellites through parameterized mathematical expressions is presented. Simulated data of observations are used during one period, and with the help of Estimation Theory of Parameters and particularly the Kalman filter technique, the parameters of the equations are estimated. Obtained the time variation equations of the element of the orbit, this can be propagated with considerable saving of computation efforts.