Abstract
The problem of satellite formation motion is considered, described by the modified Lawden-Sedwick-Schweighart equations. The formation mission is real-time Earth observation. The primary satellite with a mass of 65 kg moves in a geostationary orbit. Three accompanying spacecrafts, positioned in the plane of the tetrahedron base, are with masses of 50 kg each. A control algorithm has been developed to ensure a sufficient level of formation stability in the presence of a disturbed reference orbit and various uncertainties, based on robust control algorithms such as H2 and H∞. The maximum control force required to maintain the satellite formation's configuration using these control algorithms is 7 mN. It is necessary to determine the types of propulsion systems that meet these requirements. Among the electric propulsion systems available on the market, such as ion engines and Hall thrusters, the specific impulse allows them to generate a maximum thrust of about 15 mN and a minimum of about 6.6 mN. Comparing the obtained thrust values with the control force required to maintain the satellite configuration, it can be concluded that the developed mathematical framework can be successfully implemented in the satellite formation’s control system, ensuring the control of satellite motion and their relative positions.