FIELD: power engineering.
SUBSTANCE: invention relates to solar batteries (satellites) of space vehicles (spacecraft). Method includes determining the angle between the normal to the working surface of the satellites and the normal to the plane of the spacecraft orbit, subject to the minimum shadowing of the satellites by the design of the spacecraft. Angle between the direction to the Sun and the normal to the plane of the orbit of the spacecraft and also the change of this angle per turn are measured. Moments of measurement depend on the moment of passage of the point under the sun of the turn and the angle between the radius vector of the space vehicle and the projection onto the plane of the orbit of the indicated normal. Unfold the SB into discrete positions of orientation to the Sun with a specified accuracy and measure the current from the SB in the light portion of the orbit loop, where some condition is satisfied, which depend on the angles indicated above. Described actions are repeated in the following sections. Monitoring of the performance of satellites is performed by comparing the values of the current SB for pairs of consecutive light areas, where the current is averaged taking into account the determined distance from the Earth to the Sun and the accuracy of the SB orientation on the Sun.
EFFECT: technical result consists in providing the same conditions for measuring the current from the SB against the background of the space flight of the spacecraft.
1 cl, 2 dwg
