FIELD: spacecraft power supply.
SUBSTANCE: invention relates to the power supply of a spacecraft (SC). The method involves turning the solar battery (SB) to achieve a minimum angle between the normal to the front surface (FS) of the SB and the direction to the Sun. Additionally, the spacecraft is deployed to the position of full illumination of the SB FS by the Sun and the brightness of the underlying terrain (UT) observed from the spacecraft is measured in visible light. The SB current is measured at the interval when the points of intersection of the line of the Earth’s horizon visible from the spacecraft with the SB plane are on the shadow part of the Earth’s surface. The performance of the SB is determined by the value of the SB current when its FS is illuminated at right angles by solar radiation of the reference brightness at the specified interval. At the same time, the current value of the solar luminous flux, the angle of its incidence on the SB FS and the specified brightness of the UT are taken into account.
EFFECT: increase in the accuracy of monitoring the performance of the SB.
1 cl, 1 dwg
