The satellite orbit determination approach involves a set of techniques which measure the satellite motion in terms of its velocity and position. In this paper, we have elaborated the method of determining an accurate ephemeris for an orbiting satellite which involves estimating the position and velocity of the satellite from a sequence of observations. To observe perturbations in the orbit due to different types of gravitational and non-gravitational effect, we have applied the prediction algorithm and analysed the changes in the Kepler's elements. Dynamic and static errors are the limiting factors for estimation techniques, such as the geo-potential model errors and atmospheric drag model errors, depending on the dynamic environment of the satellite. The proposed prediction model can help to prevent the loss of control over the satellite due to orbital variations.