METHOD OF CONTROLLING SPACECRAFT POWER SUPPLY SYSTEM Russian patent published in 2016 - IPC H02J7/00 

FIELD: electronic equipment.

SUBSTANCE: invention relates to electrical engineering, namely to self-contained power supply systems (PSS) of spacecrafts (SC), using photoelectric batteries (PB) as initial power sources, and accumulator batteries (AB) as energy accumulators. Said technical result is achieved by method of controlling power supply system of spacecraft (SC), containing a photovoltaic cell (PB) and n accumulator batteries (AB), voltage stabilizer, connected between PB and load, and n charging and discharging devices, which consists in control of voltage stabilizer, charging and discharging devices depending on PB illumination, of charge condition of all AB, input and output voltage of power supply systems (PSS); introduction of prohibition of operation of respective discharging device when minimum charge level of given AB and removal of this prohibition at high charge level of AB; generating control signal in SC on-board control system for disconnection of some on-board equipment (OE) in case of emergency discharge of several m (m ≤ n) AB to minimum charge level, inhibition of operation of all discharge devices, if output voltage of PSS falls to given threshold value; execution of memory release control signal to prohibit all discharge devices after all AB charge to specified charge level, estimating the actual maximum PSS power is followed by calculation-experimental method, for which volt-ampere characteristic (VAC), which is graphical relationship between current and voltage PB and composed by results of testing standard PB in laboratory conditions at normal ambient temperature is selected as base VAC; during normal operation of PB in SC PSS coordinates of at least n characteristic points actual PB VAC different from coordinates of base VAC in force action on PC of space factors; measurement of voltage and corresponding PB current is performed using telemetric information obtained for same temperature value and identical conditions of illumination of the PC; in order to determine coordinates of characteristic points actual VAC of PB discontinuous change modes of load current PSS by applying variable load placed in mode of charge storage batteries; coordinates of first characteristic point of VAC current and voltage values are used, corresponding to mode of supply of onboard equipment (OE) and charge (n-1) of accumulator batteries, and for determining coordinates of n-th reference point is value of similar parameters of PB corresponding supply mode only OE; for each characteristic point actual VAC voltage difference is calculated PB VAC ΔUi between base and actual curve determined at fixed value of PB current; obtained n = i values ΔUi are summed up and arithmetic mean values ΔU_WED; according to base curve makes curve of the P_PB=f(U_PB), where P_PB - PB power equal to product of PB current voltage; U_PB - current voltage value PB; this dependence value of optimum voltage (U_PB)_opt, wherein standard PB in laboratory conditions is generated maximum power; subtracted from (U_PB)_opt value ΔU_CP and design value of voltage PB U_des; value of power VAC determined at base curve for U_PB=U_des, is taken as actual maximum PB power; similar sequence of operations is performed periodically, for example in every 6 months standard operation of SC.

EFFECT: technical result is development of method of controlling power supply system of SC, making it possible to considerably reduce probability of emergency situation due to violated PSS by rapid evaluation of actual maximum power by calculation-experimental method.

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