For computation of orbital elements at the epoch, a large number of measurements including azimuth and elevation 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). Iinitial Orbit Determination (Angles-only Method) (https://www.mathworks.com/matlabcentral/fileexchange/55178-iinitial-orbit-determination-angles-only-method), MATLAB Central File Exchange. Retrieved .
The code is a good effort towards automation of orbit prediction however I cannot make it work for my particular problem. I am using the file "anglesdr.m" file. When I give it the particular inputs, it throws an error which is related to the generation of complex values in "doubler.m". I need help in this regard.
Also there almost no documentation for clarification of variables and functions used in the code.
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