The simulation results of the operation of a small spacecraft motion control system with an electrothermal microdrive

Abstract

Abstract The work simulates the operation of the motion control system of a small spacecraft. The main Executive body of this system is the engine-flywheel. It is proposed to use an electrothermal micro-motor to reduce the kinetic moment of the flywheel motor. In emergency situations, it can be used as the main Executive body of the management system. A comparative analysis of the advantages and disadvantages of using magnetic actuators and electrothermal micro-motor to reduce the kinetic moment of the flywheel motor. Conclusions are drawn on the feasibility of their application for various small spacecrafts.