Modeling of spacecraft electrical power supply for transients currents and voltages calculations after electrostatic discharge impact

Modeling of spacecraft electrical power supply (EPS) after electrostatic discharge (ESD) impact on unshielded bus «plus» of solar array (SA) electrical interface and on spacecraft (SC) case through the magnetospheric plasma was carried out. On the basis of this model levels for current and voltage impacts on the most interesting electrical circuit points (energy convert complex (ECC) inputs and outputs, ECC units, decoupler SA equipment) were determined. Recommendations and proposals for further analytical and experimental research were formulated to clarify the ESD and SC EPS models.