System Identification of Extended Kalman Filter for LEO Satellite Orbit Motion

In this study, the orbit propagation simulator of the Vanguard 2 satellite, a low orbit satellite, was developed and the position and speed information of the satellite in different frames was found. Measured position and velocity data of the satellite comes from the inertial navigation system (INS) and global positioning system (GPS) were generated based on simulation. The measured position and velocity values of the satellite were combined and estimated using the extended Kalman filter algorithm with INS/GPS integration. The measurement covariance matrix value, which affects the estimation accuracy and whose value is not known exactly, was found through the system identification study. All study has been carried out in the MATLAB/Simulink environment.