FIELD: transport.
SUBSTANCE: invention relates to electric power supply systems of spacecraft. The method includes presetting the solar battery (SB) design angular rotation velocity exceeding the angular velocity of aircraft circularisation around the Earth by an order and more. In this process, electric current generated by SB is measured, SB rotation period is determined from mismatch between its design and preset angles down in this mismatch. SB is rotated prior to control start up to the moment of starting to reduce achieved greatest amount by means of current. The design SB angle is assigned the value of preset angle, herewith, the design angle is calculated during SB rotation as product of design angular velocity by SB rotation time. Time points of maximum current generation between moments of rotation termination and starting the next rotation are stored in memory. The design angle is corrected for amount of: error correction depending on aircraft angular orbital velocity, stored in memory time values at the moment of SB rotation termination and at the moment when current generated by SB reaches maximum value, as well as on SB rotation period. Design angle is increased or decreased by error correction value when SB is rotation during time reckoning in direction of increasing or decreasing angle respectively.
EFFECT: method functionality enhancement while providing correct SB orientation by generated by it current in the absence of information about SB angular position.
5 dwg
