| 摘要 |
FIELD: electricity.SUBSTANCE: invention relates to equipment of electrical rocket plasma propulsion systems (ERPDU) and can be used for qualification tests of ERPDU components - plasma engines (PE) and power supply and control systems (PSCS) for stability to impact of electrostatic discharges caused by volume electrisation of spacecrafts. When using the capacitor accumulator as a source of static electricity its discharge current into the tested equipment (TE) is divided into inductive and capacitive-inductive components by means of additional capacitance, inductance and two isolation diodes, forming the duration of the simulating pulse front, and from the moment of levelling of voltage in additional and accumulative capacitances their energies are summarize and sent to TE through series connected inductance, thus completing the pulse formation in general.EFFECT: expansion of functionality of formation of electric simulating impulses that allows to raise the level of qualification of plasma engines and power supply and control systems for resistance to electrostatic discharges.2 cl, 2 dwg |
