Development of a control and measurement device for the supply of working gas for laboratory testing of electric thrusters for space applications.

Abstract

According to the analysis of leading experts in the space industry over the past 10 years, the number of satellites operating in Earth's orbit has increased by 252%, from 958 (at the beginning of 2010) to 3371 (in 2020) [1, 2]. Most modern spacecraft are equipped with onboard propulsion systems, which not only extend the active operating period by maintaining orbit parameters but also significantly enhance the spacecraft's functionality through changes in its orientation and maneuvering. Electric propulsion systems (EPS) are increasingly used as onboard propulsion systems. An electric propulsion system typically consists of an electric thruster, a propellant feed system, an electric power conversion system, and a control system. The development of EPS components requires extensive laboratory research to simulate the operating conditions of EPS components in space.

For laboratory research and testing of EPS components and subsystems, a test bench system is used to supply propellant, which must provide regulation and measurement of propellant flow rates into the anode block and the hollow cathode of the Hall effect thruster. During laboratory testing and optimization of modes and parameters of electric thrusters, it is necessary to vary the propellant flow rates widely and have the ability to measure and record their current values [3]. Therefore, research aimed at accurately measuring propellant flow rates on the test bench under various conditions is scientifically relevant.