METHOD OF CONTROLLING AUTONOMOUS POWER SUPPLY SYSTEM OF SPACECRAFT

摘要

FIELD: electronic equipment.;SUBSTANCE: invention relates to electrical engineering, specifically autonomous power systems (SEP) of spacecraft (SC), using as primary sources of energy photovoltaic batteries (BF), and as energy storage - accumulator batteries (AB). Technical result is achieved by that control method of autonomous power supply system of spacecraft, comprising a photovoltaic cell and n accumulator batteries, a voltage stabiliser, connected between the BF and load, and n charging and discharging devices, which consists in control of voltage stabiliser, charging and discharging devices depending on illumination of BF, charge condition of all AB, input and output voltage of power supply systems (SEP); introduction of prohibition of operation of respective discharging device when minimum charge level of given AB and removal of said prohibition at high charge level of battery; generating control signal in spacecraft on-board control system for disconnection of some on-board equipment (BA) 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 SEP falls to a given threshold value; execution of memory release control signal to prohibit all discharge devices after all AB charge to specified charge level; selecting value of nominal input voltage corresponding voltage in operating point of volt-ampere characteristic (VAC) of BF, based on value of its rated power required to provide for normal operation mode of operation of electric power for supply of BA and charge of all AB; setting and maintaining if necessary, input voltage in a working point of BF VAC with help of extreme BF power regulator in case of power consumption of BA rated value; implementing change in voltage in operating point of BF VAC automatically or discretely at a predetermined threshold values of input voltage on influence temperature and degradation parameters of photoelectric converters of electrical characteristics of BF is reduction of its maximum power that make actual BF VAC at specified temperature of photoelectric converter, approximating coordinates of its characteristic points, obtained by measuring actual voltage values and corresponding BF current; coordinates of first characteristic point coordinates are received BF VAC corresponding to mode of short-circuit of BF, when input voltage is equal to zero, measurement of parameters of BF is carried out in laboratory conditions, as coordinates of second characteristic point coordinates are selected, corresponding to typical operation of BF on light spacecraft orbit section; coordinates of characteristic points corresponding to maximum BF power take-off mode is set, including in standard operation of extreme BF power regulator, which is voltage stabiliser; coordinates of other characteristic points BF VAC is determined by load current change SEP; variable load AB is used in charge mode; compared BF VAC produced in laboratory conditions at normal ambient temperature, and actual BF VAC corresponding to mode of standard operation of spacecraft at maximum illumination panels of BF; actual BF VAC make calculation-experimental method; results of comparing BF VAC forecast energy balance SEP and planning of operation program target equipment; similar sequence of operations are repeated periodically, for example in every 90 days standard operation of spacecraft.;EFFECT: technical result of invention is to provide a method for controlling an autonomous spacecraft power system, which significantly reduces likelihood of an emergency due to violation of energy balance of SEP.;1 cl, 3 dwg