Features of deorbiting geostationary satellites

The results of numerical simulation of the process of the disposal of a spacecraft from a quasi-geostationary orbit to a graveyard orbit with a height of about 280 km are presented. The calculations were carried out for a satellite with parameters very close to those of the Kazakh geostationary satellite Kazsat-2. Calculations have shown that, when using a stationary plasma thruster, the satellite reaches the disposal orbit in two days. And when a gas thruster is used, it will take eight days. At the same time, fuel consumption is approximately 60 kg more than in the case of SPT-70 and amounted to 61.826 kg. Taking into account this factor is very important when planning the movement of a satellite into a disposal orbit. Although raising the satellite’s orbit will cause a westward drift, the change in longitude over the entire withdrawal period does not exceed 0.3 degrees.