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 then the SB to the position at which the points of intersection of the line of the Earth's horizon visible from the spacecraft with the plane of the SB are on the shadow part of the Earth’s surface. The SB current is measured at an interval when the component of the SB current from the illumination of its FS by the light flux emanating from the Earth does not exceed the error of measuring the SB current. The performance of the SB is monitored based on the results of comparing the current and previously obtained, at the specified interval, values of the SB current when its FS is illuminated at right angles by solar radiation of the reference brightness. At the same time, the current value of the solar luminous flux in the spacecraft orbit is taken into account.
EFFECT: increase in the accuracy of monitoring the performance of the SB.
1 cl, 1 dwg
