Long-Term Stability of Satellites in Non-Equatorial Orbits

Abstract

In the present day, around 9,900 satellites are orbiting the Earth. To further understand and model these orbits, this paper introduces a dynamics model aimed at achieving higher fidelity in orbit simulations, accounting for different angles, velocities, positions, and accelerations. Additionally, perturbations in space and their effects on various types of orbits are studied. Three major perturbations are tested: third-body perturbations, Earth's oblateness (J2 effect), and atmospheric drag. After plotting these orbits, it was discovered that the most significant perturbation to Earth-orbiting objects is the J2 effect, followed by atmospheric drag and third-body perturbations. While these perturbations may seem to have a minuscule effect on orbits, the numbers, especially those resulting from the J2 effect, can be incredibly significant in orbital mechanics, where calculations must be precise. The insights gained from this project highlight the necessity of using advanced models and real-time data to refine predictions and ensure satellites' precise and stable operation. By continuously improving the understanding and modeling of these perturbations, the reliability and effectiveness of satellite missions are enhanced, which are integral to space exploration, communication, navigation, and Earth observation.