초록 ▼

There is provided a rocket trajectory estimating method comprising the steps of: measuring a GLOS angle of a flying rocket a tracking system; passing the GLOS angle data through a batch filter to reduce noises; estimating a rocket trajectory on the basis of the GLOS angle data, the noises of which h

There is provided a rocket trajectory estimating method comprising the steps of: measuring a GLOS angle of a flying rocket a tracking system; passing the GLOS angle data through a batch filter to reduce noises; estimating a rocket trajectory on the basis of the GLOS angle data, the noises of which have been reduced; passing the resulting rocket trajectory data through a Kalman filter to reduce biases; and estimating the rocket trajectory again on the basis of the corrected GLOS angle data and the positional information of the tracking system. Thus, there is provide a rocket trajectory estimating method capable of reducing observation errors (noises and biases) of a tracking system of a passive ranging system, which does not have need of any laser range finders, to enhance the accuracy of rocket trajectory estimation.

대표청구항 ▼

[ What is claimed is:] [6.]6. A rocket identifying method comprising the steps of:measuring a GLOS angle of a flying rocket by a tracking system;passing the resulting GLOS angle data through a batch filter to reduce noises;estimating a rocket trajectory on the basis of said GLOS angle data, the nois

[ What is claimed is:] [6.]6. A rocket identifying method comprising the steps of:measuring a GLOS angle of a flying rocket by a tracking system;passing the resulting GLOS angle data through a batch filter to reduce noises;estimating a rocket trajectory on the basis of said GLOS angle data, the noises of which have been reduced;passing the resulting rocket trajectory data through a Kalman filter to estimate biases, and correcting said GLOS angle data by eliminating the biases estimated by the Kalman filter;estimating said rocket trajectory again on the basis of the corrected GLOS angle data, the biases of which have been eliminated, and a positional information of said tracking system; andoutputting estimated values of orbital elements of the finally estimated rocket trajectory from said Kalman filter, and identifying said rocket by comparing the outputted estimated values of orbital elements with values of orbital elements of various rocket trajectories.