MATLAB Code Implementation for Satellite and Orbit Simulation

This program aims to simulate satellites and their orbital dynamics using MATLAB to deliver an enhanced learning experience. The implementation covers fundamental orbital mechanics concepts, including how orbital parameters characterize satellite motion and the physical laws governing satellite trajectories around Earth. The code demonstrates practical MATLAB applications for orbital simulation, featuring numerical integration methods for trajectory propagation and 3D visualization tools for orbit plotting. Key algorithms include gravitational force calculations using Newton's laws, coordinate transformations between Earth-centered inertial (ECI) and Earth-centered Earth-fixed (ECEF) frames, and orbital element conversions. Through analyzing simulation outputs, users can examine orbital characteristics such as apoapsis/periapsis evolution and perturbation effects. This program provides comprehensive understanding of satellite operational principles and implementation methodologies, offering valuable support for future research and academic pursuits in aerospace engineering.