METHOD OF CONTROL OVER SPACECRAFT SOLAR BATTERY ORIENTATION WITH LIMITATION OF SOLAR BATTERY TURN ANGLE Russian patent published in 2014 - IPC B64G1/44 

FIELD: transport.

SUBSTANCE: invention relates to spacecraft electric power supply with the help of solar batteries. Proposed method comprises definition of preset angle of solar battery orientation to the Sun by measured angular position of normal to battery working surface and computation of design angle relative thereto. Solar battery is spinned in direction of decrease in mismatch between preset and design angles. Solar battery acceleration angle (α_AC) and deceleration angle (α_DEC) are defined. Design angle is corrected when angle transducer readings vary by discrete sector of solar battery turn. Threshold of operation and drop-away (α_T) and (α_D) are set to terminate battery spinning if mismatch between preset angle and current angle increases but not over α_T. Solar battery angular velocity is set or the order and larger than maximum angular velocity of spacecraft revolution around the Earth while discrete sector magnitude is set to smaller than α_T. Solar battery working angle (α_W) is set provided that α_T < α_W < (α_"ГОР" - 2·(α_AC + α_DEC)). Angular position of closest beam of angle α_W is assigned to preset angle if direction to the Sun in projection to the plane of spinning of said normal is located outside of α_W. Is angular position of said normal is outside α_W to vary in direction of increase of angle relative to nearest beam of angle α_W, failure warning is generated to terminate control over solar battery.

EFFECT: ruled out jamming and breakage of solar battery panels or spacecraft onboard hardware at turns from 90° to 180°.

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