Theoretical explanation and calculation for Keplerian orbital elements in low earth orbit and geostationary orbit

After the detailed study about orbits, GEO is chosen based on developments to be done in the inclination and eccentricity. Hohmann transfer is needed to attain the GEO, so delta-V calculation is carried out for four different cases and proved the lower delta-V total. To extend further, calculations for orbital elements and perturbations to be done, to analysis the satellite’s position in its respective orbit. By determining these values, they can be entered in the software and orbit design will be optimized. In this paper, theoretical calculation for orbital elements, brief explanation of orbital man oeuvres and how to determine it will be studied. And calculation for six keplerian orbital elements for both LEO and GEO will also be carried out. The importance of epoch both in practical and software cases are explained in a detailed manner. The three dimensional trajectories which will be useful to locate the satellite’s position and direction are described in the manner how the software works on it.