FIELD: aviation.
SUBSTANCE: invention relates to electric generation systems of spacecraft (SC). The method comprises a turn of solar panels (SP) of SC with their working surfaces to the sun. The maximum output power of the SP is determined by measuring the current and voltage of the SP at times when radiation reflected from the Earth is incident on the front and/or back side of the SP. The SC is additionally turned until angles between direction vectors to the sun and normal vectors to the SC segmental surfaces visible from the SP working surfaces reach the value of ≥ 90°.
EFFECT: reduction of the radiation reflected from the spacecraft surface influence on measurements of solar panel characteristics.
2 dwg
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