Third Body Perturbation Effect on Low Earth Orbit Satellite (GEOS-17)

Abstract

Satellite communication systems have become an important element of the global telecommunications infrastructure, providing data, internet access, telephone, and navigation services to billions of people across the world. In this work, the analytical technique for third body perturbation on GEOS-17 orbit satellite computed for a long period At a time interval of 360 days, the dynamic development of Low Orbit is considered for different values of Eccentricity (𝑒 = 0.05, 𝑒 = 0.6, 𝑒 = 0.89). It was accomplished by utilizing the numerical output results from the celestial mechanics' version 1 software program package. Numerical motion simulations were performed using the Celestial Mechanics software program SATORB module (Beutler, 2005) created at the University of Bern's Institute of Astronomy. With input data given by the Two-Line Elements (TLE). Represented by six orbital elements and three Coordinates axis and three acceleration components which were used to solve the equation of motion analytically by variation of parameters equations (VOP) using a technique known as collocation method, also Matlab (2018) is used for analysis and plot the given figures The results indicated that the greatest effect is at highly elliptical orbit (𝑒 = 0.89) for orbital elements, coordinates axis and acceleration components due to orbit propagation and attractions forces.