Simulation means of electrostatic discharges in the system “stationary plasma thruster - transformation and control system”

The elements of construction of electric propulsion system of spacecraft (SC) correction can accumulate electro- static charge due to interaction with the magnetospheric plasma. The impact of electrostatic discharges on the electri- cal circuit of the correction system can lead to failures of the transformation and control system (TCS). Particular attention is currently being paid to solving the problems related to the impact of electrostatic discharges on electric circuits of the power conditioning units, designed for power supply and control electric propulsion thrusters of space craft correction. Due to the design of the propulsion subsystem thrusters it is impossible to solve the problem of electric charge impact on TCS electric circuits through shielding these circuits. Therefore the impact of electrostatic discharges on electric circuits from the propulsion subsystem thruster is considered to be one of the factors determining the reliability and failure-free operation of TCS and, consequently, of the overall spacecraft propulsion subsystem. This problem is important today due to the following: the widespread use of electric propulsion thrusters in GEO spacecraft correction systems, the implementation of new TCS design and technical solutions suitable for spacecraft unpressurized platforms, the implementation of new electronic component base. The paper addresses the simulation means of electrostatic discharges occurring on the ceramics of the stationary plasma thruster and impacting TCS electric circuits, in particular the test equipment for generating high-voltage pulses, which allows replacing long-term and expensive tests performed on vacuum test benches. The paper contains the review of validation test results for TCS means of protection from electrostatic charge effects using high-voltage pulse generat- ing (HVPG).