Abstract
A distinctive feature of this work is to select magnetic system parameters to stabilize nano-satellite of CubeSat format, taking into account various constraints. Analysis of the physical conditions and technical problems associated with the resource constraints of this class of spacecraft was performed. Control of rotational speed and orientation of the rotation axis is made by magnetic coils interacting with the magnetic field of the earth. Results of the simulation of the satellite motion relative to the center of mass at using the proposed control algorithm “B-dot” are demonstrated. We consider two autonomous algorithms of control by current coils. To work with orientation magnetic system using the first algorithm it is necessary to evaluate the vector of the angular velocity of the satellite. The second algorithm does not require evaluation of the angular velocity. The paper also analyzes the energy consumption of the orientation magnetic systems depending on the selection of the desired direction of the rotation axis to stabilize very small CubeSat spacecraft.