Geostationary orbital injection of a spacecraft by the combined method

Relevance of the work is determined by the increased competition in the global market development of satellites, which requires the reduction of costs for the development and spacecraft launching. The obvious way to cut costs is to reduce the launching mass of the spacecraft, that allows us to apply to spacecraft launching into geostationary orbit cheaper launch vehicles of the middle class, or to launch several space vehicles with one launch vehicle. An alternative solution to this problem is the combined method of spacecraft removing. Combined method of spacecraft removing has the advantage of insertion time regarding the method of removing using only the electric propulsion thrusters, regarding the method of removing by chemical two-component propulsion thrusters - the amount of fuel. Consequently, the combined method of removing will allow the spacecraft to move quickly through the area of the inner radiation belt of the Earth using the two-component chemical thrusters and electric propulsion thrusters for further removing spacecraft on operational orbit. The aim of research is to assess the effectiveness of removing the spacecraft on geostationary orbit by the combined method, the optimization of the mass of fuel for removing. As the results of the performed work the following things can be considered: optimization criteria of the combined method, the method of optimization of the fuel mass and the corresponding set of programs in MatLab. Also, the following calculations and analysis of the results were carried out: launch spacecraft of various launching mass by combined method, using launch vehicle “Proton-M” with the upper stage “Breeze-M”, the Baikonur сosmodrome, Kazakhstan, and with the help of the launch vehicle “Falcon-9v1.1” cape Canaveral, the USA. In conclusion, according to the article launching with the help of launch vehicle “Proton-M” with the upper stage “Breeze” has a number of advantages than foreign launch vehicle.