Different method for optimal low-thrust control of release and retrieval of a concomitant satellite

A concomitant satellite revolves around its main satellite, serving and observing it. The distance between the two satellites is usually about 1 km. We propose a new method for the optimal low-thrust control of release and retrieval of a concomitant satellite. We control the release and retrieval movement with a Newton grade thrust - a very low thrust that is constant in value and works continuously. We use the Minimum Principle in the optimal control theory to establish a mathematical model for the optimal control of release and retrieval from the usually used C-W equations. Then we obtain a convenient analytic solution, on the assumption that the two satellites run along equally high orbits. The end time of the motion is determined and this determination can be done quite simply with the Newton iteration method. We give a numerical simulation example. Simulation results, show preliminarily that our method for the optimal low thrust control of release and retrieval movement of concomitant satellite is feasible.