Close to optimal solutions of exact equations of motion of the electrically propelled spacecraft in Newtonian central gravity field

An approach is discussed of construction of close to optimal numerical solution of motion equations of a low thrust space vehicle, which realize multiturn orbit transfer in the Newtonian central gravity field. For this purpose we use the approximate solution, constructed by the averaging method. Both cases of variable and constant in magnitude rocket thrust are under consideration. The efficiency of the proposed approach is illustrated for example of interorbital transfer with simultaneous changing of the major semiaxis, eccentricity and orbit inclination.