SPACECRAFT POWER SUPPLY SYSTEM Russian patent published in 2020 - IPC H02J7/34 

FIELD: electrical engineering.

SUBSTANCE: application in the field of electric engineering at designing and creation of power supply systems of automatic spacecrafts on the basis of solar and accumulator batteries. Spacecraft power supply system includes a solar battery; main accumulator battery of N accumulators; microcomputer; discharge device; a charging device, the first output of which is connected to the positive bus of the solar battery, and the second one – to the first output of the discharge device; load, the first lead of which is connected to the second terminal of the discharge device, and the second one – to the negative bus of the main storage battery of N accumulators and to the negative bus of the solar battery; unit for control and alignment of accumulators, the first output of which is connected to the first input of microcomputer, (N + 1) outputs – with accumulators of the main accumulator battery from N accumulators, and input – to the first output of microcomputer, the second output of which is connected to the first input of charging device. Additionally, there is a unit of N shunting bypass switches, the inputs of which are connected to the third output of the microcomputer, and the outputs – in parallel to each accumulator of the main accumulator battery of N accumulators; additional accumulator battery of n accumulators, negative terminal of which is connected to positive bus of main accumulator battery of N accumulators; a unit of n shunting bypass switches, the inputs of which are connected to the fourth output of the microcomputer, and the outputs are connected in parallel to each accumulator of an additional accumulator battery of n accumulators, a unit of n consecutive bypass switches, the inputs of which are connected to the fifth output of the microcomputer, and the outputs are in series with each additional storage battery of n accumulators and to each other, wherein last output (5-n) is connected to the second terminal of the charging device, the series voltage regulator, the first input of which is connected to the first terminal of the charging device, and output is with first load output, extreme power controller with control shaper, first input of which is connected to first lead of charging device, second input is connected to first load terminal, first output is connected to second input of charging device, and second output is connected to second input of series voltage regulator, generator of single current pulse, first output of which is connected to positive bus of solar battery, second output is connected to the second terminal of the charging device, the third output is connected to the negative bus of the solar battery, and the fourth output is connected to the sixth output of the microcomputer, the thermal control system, the input of which is connected to the seventh output of the microcomputer.

EFFECT: higher energy efficiency and longer life of a power supply system of a spacecraft.

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