METHOD OF CONTROL OVER SPACECRAFT SOLAR BATTERY ORIENTATION WITH CONTROL OVER SPINNING DIRECTION AND CONTINUOUS CHANGE OF DATA ON SOLAR BATTERY ANGULAR POSITION

FIELD: transport.SUBSTANCE: invention relates to spacecraft electric power supply with the help of solar batteries. Proposed method comprises definition of preset and current angles of solar battery orientation and solar battery angular velocity (?). Design angle is computed to assign measured angle magnitude thereto and memorised prior to start of control over solar battery. Solar battery is spinned in direction of decrease in mismatch between preset and design angles. Defined are angles of solar battery acceleration and deceleration (t, ?) and threshold (t, ?) and maximum tolerable angle of its deflection (?) proceeding from minimum tolerable currents of solar battery. Said angles are used to set operation threshold (?). The latter exceeded, said mismatch is generated. The latter is not taken into account if lower than drop-away threshold (?). The latter reached, solar battery spinning is terminated. Solar battery design angle is corrected with the limits of one discrete sector of solar battery spinning circle. Discrete sector magnitude depends of angles ?, ?and ?. Depending upon ?and ?threshold of the interval of control over continuous variation of data on solar battery angular position is set. Count of said interval is made if current measured angle differs from memorised one by more than one discrete sector and is terminated otherwise. Threshold of the time of control over solar battery spinning is set depending upon t, t?, ?and discrete sector magnitude. This time is counted at zero time of control over continuity is sign of mismatch between measured and memorised angles dose not satisfy the solar battery preset direction of spinning. Otherwise, count is terminated to zero the time of control of spinning direction. Note here that when measured angle varies by one discrete sector, angular angle of boundary between discrete sectors is taken to be design angle to assign new measured angle to memorised angle. In case the time of control over continuity or that over spinning direction exceeds its threshold, failure signal is generated to terminate control over solar battery.EFFECT: higher survivability and efficiency.3 dwg Изобретение относится к системам электроснабжения космического аппарата (КА) с помощью солнечных батарей (СБ). Способ включает определение заданного и текущего углов ориентации СБ и угловой скорости (ω) СБ. Вычисляют также расчетный угол и перед началом управления СБ присваивают ему значение измеренного угла, который запоминают. Вращаю