Analysis of the efficiency of electric-jet engines for keeping a low orbit of a small spacecraft

Abstract

The problem of maintaining the flat parameters of the working orbit of a small spacecraft using an electric thruster is considered. In low working orbits, due to the Earth’s atmosphere, aerodynamic forces act on the spacecraft, which cause a decrease in the radius of the orbit and the end of the target functioning. The analysis of the time parameters of the cyclogram for maintaining the working orbit of a small spacecraft with an electric jet engine is carried out taking into account the variability of the atmosphere density. The cyclogram consists of sections of passive movement and active movement under the action of a small engine thrust. For the satellite under study, the thrust parameters of the electric jet engine were selected, which allow the correction of the plane parameters of a low orbit. Using the characteristics of the thrust and specific impulse of an electric jet engine, we calculated the fuel reserves for correction over a long period of time. The results of the analysis show that it is effective to use an electric jet engine in terms of fuel consumption for correction.