For computation of orbital elements at the epoch, a large number of measurements including azimuth,elevation and range are gathered at tracking stations.
Here, I have used 46 sets of GEOS3 satellite measurements for 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 times of all measurements in an iterative procedure and the epoch's state vector is corrected at each stage.
Meysam Mahooti (2021). Initial Orbit Determination (Least Squares Method) (https://www.mathworks.com/matlabcentral/fileexchange/55626-initial-orbit-determination-least-squares-method), MATLAB Central File Exchange. Retrieved .
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