Algorithms of the control programs formation for the Earth remote sensing spacecraft

In order to meet the targets of the Earth remote sensing, it is required to form, change and maintain the working orbits of the remote sensing spacecraft. The long-term existence of modern space remote sensing systems (up to 20 years) requires the performance of these maneuvers with minimal fuel consumption. Modern electric propulsion systems have a high specific impulse (15000-70000 m/s), which ensures the fulfillment of these requirements. In addition, they meet the requirement of the operation duration. In recent decades, the optimal control theory by the electric propulsion spacecraft in near-Earth orbits has been developed. However, obtaining optimal control programs is a long and difficult computational process. The work devotes to the analysis of existing optimal solutions and the development of stable algorithms for the remote sensing control programs formation for a wide class of dynamic maneuvers.