Dual satellite image simulation based on TLE and SGP4

Abstract

A certain model should be used to predict and track the space objects that may affect the operation of satellites. In this paper, the Two-Line Elements (TLE) and the Simplified General Perturbations 4 (SGP4) models are used to calculate the position and velocity vectors of satellite A/B in the True Equator Mean Equinox (TEME) coordinate system and the Earth-Centered Inertial (ECI) system. Satellite A is selected as the observation platform to carry the camera, and the imaging positions of target satellite B on the camera of satellite A in the TEME and ECI coordinate systems are calculated respectively. The imaging trajectories are superimposed to generate several turns. The difference between the imaging positions in TEME and ECI coordinate systems is calculated, and the influence of the Earth's precession and nutation on the imaging trajectory is analyzed.