METHOD FOR DETERMINING THE OUTPUT POWER OF SOLAR PANELS OF SPACECRAFT

摘要

FIELD: electricity.;SUBSTANCE: invention relates to a power supply of spacecraft (SC) with solar batteries (SB) having a positive power output of its back surface. The method includes measuring the height (H) near-circular orbit satellites and the angle (ε) between the direction of the Sun and the spacecraft geocentric radius vector. When ε is in a certain range depending on the H, the angles (f₁,f₂). The semi-zone sensitivity SB work and back surfaces and the maximum value of the angle (f₁*) between the normal to the working surface SC and the direction to the sun, - SC unfold to the position at which the radiation enters the Earth Security is said zones of sensitivity. This position corresponds to the reconciliation of said normal to the plane containing the direction of the Sun and the radius vector of the spacecraft. The angle (ρ) between this normal and the radius vector of the spacecraft is in the range that depends onε,f₁,f₂,f₁* H and the angle (γ) between the directions of the SC in the nadir and the nearest point to the spacecraft terminator. In this position, the measured voltage, current and power output SC and given angles ε and ρ.;EFFECT: minimization of the impact of the Earth's radiation in determining the power output of solar cells.;1 dwg