For the computation of orbital elements at the epoch, a large number of measurements including azimuth, elevation and range are gathered at the tracking stations.
Here, I have used 18 sets of GEOS3 satellite measurements for the initial orbit determination. First of all, initial guess of satellite's state vector is computed from three sets of azimuth and elevation applying Double-R-Iteration/Gauss method. Then, the state vector is propagated from epoch to the time of first measurement and is updated. After that, the updated state vector is propagated to the time of next measurement and is updated again. This procedure continues until the time of last measurement. Finally, the updated state vector at the time of last measurement is propagated to the epoch.
Meysam Mahooti (2019). Initial Orbit Determination (Extended Kalman Filter) (https://www.mathworks.com/matlabcentral/fileexchange/55627-initial-orbit-determination-extended-kalman-filter), MATLAB Central File Exchange. Retrieved .
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Revised on 2016-11-21.
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