Gravitational Perturbation Influence on High Altitude Satellite for different Inclination

Abstract

Satellites have become such a vital part of our daily lives that we take for granted many of their functions, such as global positioning system (GPS) navigation and images of weather systems collected from orbit. In this work, The analytical method for third body perturbation on high Earth orbit satellites was investigated in this study for different inclinations (𝑖 = 1.71, 𝑖 = 5, 𝑖 = 10, 𝑖 = 23, 𝑖 = 25) across two revolution periods computed for short and long periods, Using the program celestial mechanics version 1 module (Beutler 2005) with input data given by the Two-Line Elements (TLE) created at the University of Bern's Institute of Astronomy. To determine the third body perturbation on Earth satellite using the collocation method. By analyzing the variation in the orbital elements, geocentric Coordinates and acceleration components by Matlab 2018, There was no discernible change in the coordinate system or acceleration components, which appeared to be secular in both results, change, and effect of perturbation has greatest point at Geocentric equatorial coordinates combinations. The conclusion indicates that the Moon perturbation has the most significant impact on orbital elements; furthermore, the satellite with increasing altitude has increasing the amount of perturbation.