MATLAB Implementation for Satellite Coordinate Calculation Using Broadcast Ephemeris Parameters

To calculate satellite coordinates, a MATLAB program must be developed that processes the 17 broadcast ephemeris parameters. These parameters include orbital elements such as semi-major axis, eccentricity, inclination, and others, which are essential for determining the satellite's position in Earth-centered Earth-fixed (ECEF) coordinates. The implementation typically involves solving Kepler's equation iteratively to compute the satellite's true anomaly, followed by coordinate transformations to obtain the final position. The program can be optimized by integrating advanced algorithms like Kalman filtering, which uses recursive estimation to improve prediction accuracy by reducing noise and errors in the ephemeris data. Key MATLAB functions for this implementation may include `fsolve` for solving nonlinear equations, coordinate transformation functions like `ecef2lla` for converting to latitude, longitude, and altitude, and custom Kalman filter functions to handle state estimation. This enhanced program is suitable for applications in navigation systems, satellite tracking, and communication technologies, providing a robust solution for accurate satellite positioning.