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The transition from low Earth orbit 200-1500 (km) to geostationary Earth orbit 42162 (km) was studied in this work by many methods of transfer. The delta-v requirement (∆v), the time of flight (∆t), the mass ratio of propellant consume (∆m/m) and total mass was calculated for many values altitude in the same plane also when the plane is change. The results from work show that (∆v) that required for transfer when the plane of orbit change is large than (∆v) required when the transfer in coplanardoi:10.24996/ijs.2018.59.1a.21 fatcat:xqqadqoypbajvjfjq5ex2dnbqa