1. A method for providing an extended propagation ephemeris model for a satellite in Earth orbit comprising: obtaining a satellite's orbital position over a first period of time; applying a least square estimation filter to determine coefficients defining osculating Keplarian orbital elements and harmonic perturbation parameters associated with a coordinate system defining an extended propagation ephemeris model that can be used to estimate the satellite's position during the first period, wherein the osculating Keplarian orbital elements include semi-major axis of the satellite (a), eccentricity of the satellite (e), inclination of the satellite (i), right ascension of ascending node of the satellite (Ω), true anomaly (θ*), and argument of periapsis (ω); applying the least square estimation filter to determine a dominant frequency of the true anomaly; and applying a Fourier transform to determine dominant frequencies of the harmonic perturbation parameters.