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Initial Orbit Determination (Extended Kalman Filter)

version (17.4 MB) by Meysam Mahooti
Initial orbit determination applying Extended Kalman Filter


Updated 16 Mar 2020

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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 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.

Cite As

Meysam Mahooti (2022). Initial Orbit Determination (Extended Kalman Filter) (, MATLAB Central File Exchange. Retrieved .

MATLAB Release Compatibility
Created with R2019b
Compatible with any release
Platform Compatibility
Windows macOS Linux

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