Kartal, Seda (Karadeniz)Kaya, Yasin BurakNergiz, FatmaOzbag, EsraYilmaz, YagnurDar, Tayfun2024-02-232024-02-232023979-8-3503-2302-3https://doi.org/10.1109/RAST57548.2023.10197979https://hdl.handle.net/20.500.12452/1373810th International Conference on Recent Advances in Air and Space Technologies (RAST) -- JUN 07-09, 2023 -- Istanbul, TURKEYIn this study, the mathematical model of orbit propagation motion for geosynchronous equatorial orbit called GEO satellite was obtained using Kepler's parameters comes from TLE (Two Lines Element) data. It is implemented to five GEO satellites (31 degrees E, 42 degrees E, 50 degrees E) in Simulink environment. Ground stations in four different regions of Turkey (east, west, south, north) and in the eastern city outside of Turkey's were modeled with ECEF (Earth-Centered Earth-Fixed) frame. The GDOP values were calculated and analyzed from the distances between each GEO satellite and each ground station. Lowest GDOP value reached in the eastern city outside the country. All study is modeled in MATLAB/Simulink environment.eninfo:eu-repo/semantics/closedAccessGeo SatelliteOrbit Propagator ModelGdopPositioning SystemGround StationConference Object2-s2.0-85168426096WOS:00105507460014310.1109/RAST57548.2023.10197979