METHOD TO CONTROL POWER SUPPLY SYSTEM OF SPACECRAFT WITH LARGE ACTIVE SHELF LIFE Russian patent published in 2017 - IPC H02J7/35 

FIELD: electricity.

SUBSTANCE: according to the method of controlling the spacecraft power supply system, containing the photovoltaic battery, and n AB, the voltage stabiliser, and n charging and discharging devices, control the voltage stabiliser, charging and discharging devices, depending on the input and output voltages of the EDS; control the degree of charging AB; introduce the appropriate charging device operation prohibition, when the maximum charge level of this AB is reached and remove this prohibition with the decrease in the charge level; introduce the appropriate charging device operation prohibition, when the specified minimum level of this AB charging is reached and remove this prohibition with increasing the level of this AB charge; control the output voltage by means of the threshold sensor. At the emergency discharge of several m (m≤N) AB up to the minimum level of charge, form the control signal to the on-board control system of the spacecraft for switching off the part of the on-board equipment and memorize it; at the emergency discharge of all n working ABs up to the minimum level of charge, the prohibition on the operation of all discharging devices is removed; in the event that, after memorizing the control signal, the output voltage of the EDS drops to the predetermined threshold value, all the discharging devices operation is prohibited; after restoring the orientation of the photoelectricbattery (PB), the remaining included part of the onboard load from the BF is powered at the sun; the reset of the control signal memorization is made after charging of all the accumulator batteries or by the external one-time command, as the parameter for evaluating the accumulator batteries state choose the voltage of the accumulator or the group enclosed between each other parallel accumulators; to control the operating modes of the AB the corresponding control signals are generated, that differ in the magnitude of the battery threshold voltage or the group of batteries threshold voltage; disconnection of AB from the charge is performed stepwise; the introduction and removal of the prohibition for the operation of the appropriate charging device is carried out, respectively, when the temperature in any AB of the maximum allowable level is exceeded and remove when the temperature drops to the predetermined level; the introduction and removal of the prohibition on the appropriate charging device operation is carried out, depending on the temperature of the AB; control of the discharge depth of each AB is carried out with the help of the ampere-hour counters (AHC), included in the discharge-charging circuits of each n ABs. The AHC readings from all n AB summarize and determine the integral depth of the discharge; in the case of achieving the integral depth of the threshold values discharge, the appropriate control commands are formed to change the spacecraft operation mode.

EFFECT: increase of the power supply systems reliability and survivability and reduction of the emergency situations likelihood of occurrence.

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