SPACECRAFT POWER SUPPLY SYSTEM Russian patent published in 2018 - IPC H02J7/35 

FIELD: electrical engineering.

SUBSTANCE: field of application: electrical engineering. Power system of the spacecraft contains a solar battery, battery, voltage regulator and discharge device, made in the form of bridge controlled current inverters with input L-filters, rectifier, reversible rectifier, two separate matching transformers, a control system with an extreme power regulator, device for controlling the degree of charge of the battery, current sensor and load. Solar battery is connected to a voltage regulator whose output is connected to the primary winding of the first transformer. Battery is connected to a discharge device, the output of which is connected to the primary winding of the second transformer, and also to the device for monitoring the degree of charge of the battery. Secondary windings of the first transformer are connected in series, like the secondary windings of the second transformer. Transformers are designed both for matching the value of the supply voltage and voltage on the load, and to create a midpoint rectifier and a reversible rectifier connected to each other and serving as one of the poles of the voltage on the load. Second pole of the load voltage is connected to the second output bus of the rectifier and the reversing rectifier. In the scheme, summation of output currents of primary energy sources is realized. Similarly, other supply channels for loads with any voltage rating can be generated. Control impulses of transistors of voltage regulators inverters, bit device and a reverse rectifier forms the control system with which the current sensor, the battery charge state monitor and the measuring windings of the transformers are connected.

EFFECT: technical result is the elimination of the possibility of electrostatic discharges between the photodiode chains of the solar battery, reduction of voltage on secondary windings of transformers and reduction of overall power of power elements of energy-converting devices, and minimization of the mass-dimension parameters of the power supply system of an automatic spacecraft as a whole.

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