In the recent years, there has been a growing interest in using aerodynamics drag force to eliminate relative drift between satellites moving in a group. This article is devoted to the development and study of some algorithms for decentalize stabilizing the relative position of two satellites moving in a near-circular Earth orbit. A brief review of approaches and results on methods of controlling a satellite group by changing the aerodynamic drag force is given. Control algorithms based on the modal (pole placement) approach, the passification-based and variable-structure control methods, linear and time-optimal partial stabilization are developed and studied. The robustness of control systems with respect to plant model parameters is examined. The possibility of the appearance of sustained oscillations as a consequence of the control action (the aerodynamic drag) boundedness is demonstrated.