Satellite orbit determination based on gradient method

Abstract

In this paper, gradient method is applied to the problem of satellite orbit determination. We used the ground station data (range, azimuth and elevation), for calculating the satellite position vector in the ECI frame. Satellite orbit is in the elliptic shape and satellite turns in orbital plane. Hence, orbit frame (PQW) is defined. Based on representation of input data in the PQW frame, we can define an ellipse. With the characteristics of an ellipse, beside definition of cost function and optimization technique, the satellite orbit is determined. This method, which can be easily implemented in hardware with moderate computational complexity, yield an efficient satellite positioning without assuming a prior knowledge of measurement noise. The performance, accuracy and error of algorithm are checked, by a test case.

Random Error Estimation and Propagation Analysis for Satellites’ Initial Positions

“…Existing investigations determine the orbital position of the satellite by receiving satellite signals from the measuring station [8,9]. Larki et al [10] determined the satellite orbit based on the gradient method. Based on historical orbit data, Bai [11] investigated the orbit prediction error and the collision probability of space objects.…”