Strong tracking cubature Kalman filter for real-time orbit determination for impulse maneuver satellite

To solve the real-time orbit determination for impulse maneuver satellite, this paper proposes a strong tracking cubature Kalman filter (STCKF) algorithm. This algorithm uses the equivalent representation of strong tracking filter (STF) to calculate suboptimal fading factor so as to real-timely adjust the gain matrix online. In this way, residual error series are forced to be mutually orthogonalized, thus realizing the tracking of the sudden change state of strong nonlinear system. In addition, Euler predictor-corrector method is utilized to discretize the orbital dynamic equation with J
₂
perturbation, thus effectively enhancing the discretization precision of the model. The simulation results indicate that the STCKF algorithm can effectively realize the real-time orbit determination for impulse maneuver satellite with high accuracy.