FIELD: electrical engineering.
SUBSTANCE: use in the field of electrical engineering when designing and manufacturing power supply systems for automatic space vehicles. Power supply system of the spacecraft comprises solar and accumulator batteries, an input choke L, a voltage regulator made in the form of a bridge inverter on transistors, a discharge device, a charger made in the form of a bridge inverter on transistors, a first transformer with primary and secondary windings, a second transformer with primary and secondary windings, a first rectifier, a second rectifier, a control system with an extreme solar power regulator, a device for monitoring the degree of battery charge, a current sensor, a load and a switch.
EFFECT: technical result of the invention is higher reliability of the power supply system of spacecraft.
1 cl, 2 dwg
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RU2572396C1 |
Authors
Dates
2018-04-09—Published
2016-12-07—Filed