Orbital Equation Smoothing based Trajectory and Impact Point Prediction

Trajectory prediction and impact point prediction demand for high velocity accuracy of the initial prediction point, to obtain prediction precision benefit. Non-cooperative radars are usually incapable of velocity measurement. The velocity is often computed by polynomial smoothing differentiation and Kalman filtering based on the measured data, of which the accuracy is low. An orbital equation smoothing based prediction is proposed in this paper, so as to improve the precision of trajectory prediction and impact point prediction. The experimental results shows that the method can eliminate the influence of random errors and provide stable and highly accurate prediction. The method is demonstrated to perform well in practical aircraft orbit prediction and landing point prediction.