LAUSR

Abstract The article is devoted to the creation of a control system for the orbital segment of a space solar power station and the main principles of its creation. The simulation of the functioning of a demonstrational space solar power station operating in an elliptical orbit with the energy transfer in low orbit sections has been conducted and a high-precision control of the spacecraft at low altitudes has been considered. The result of the performed studies is the computational confirmation of the capabilities of the measuring, calculation and orientation to provide the required accuracy of the spacecraft orientation for demonstrating the energy transfer from orbit to the receiver system. The obtained results give grounds for the construction of a demonstrational space solar power station in the low orbit.