MATLAB-based Satellite Orbit Simulation Implementation

This MATLAB-based satellite orbit simulation implementation utilizes six classical orbital elements as fundamental parameters. These orbital elements are numerical parameters describing satellite trajectories, including semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, and mean anomaly. The implementation involves defining these parameters as input variables and calculating satellite positions through Kepler's equation solving algorithms. Key MATLAB functions like fzero or custom Newton-Raphson implementations are typically employed to numerically solve the transcendental Kepler's equation for eccentric anomaly. The computational process converts orbital elements to Cartesian coordinates using transformation matrices, enabling precise prediction of satellite positions and velocities. This simulation approach provides essential foundations for satellite communication systems, navigation applications, and meteorological satellite tracking by generating accurate orbital trajectories.