Electro-rocket ramjet thruster for compensating the aerodynamic drag of a low-orbit spacecraft

In the paper, the problem whether it is possible to use an electro-rocket ramjet (ERRJ) thruster in a correcting propulsion system of a low-orbit spacecraft (SC) is analyzed. The calculated aerodynamic drag of the spacecraft is presented for orbits of 180-280 km. Parameters of electro-rocket ramjet are analyzed and the most suitable high-frequency ion thruster is chosen for further investigation.