FIELD: transport.
SUBSTANCE: invention relates to space engineering and can be used for spacecraft (SC) manufacturing. Components are manufactured, SC is assembled of power-supply system with solar and accumulator batteries (SAB), stabilised converter with charging and discharging converters, service system module, payload, SC electric tests are carried out (functional, thermal vacuum, final tests involving SAB simulators connected to industrial network via uninterruptible power system with blocking operation of power system voltage stabilised converter charging converters by ground aids or working over charging interface without charge energy recovery to industrial network), tests for impact of mechanical loads and for control of solar and accumulator batteries coupling using standard solar and accumulator batteries are carried out.
EFFECT: SC functionality enhancement and higher reliability of its electric testing process.
1 dwg
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