We consider the features of time-optimal multi-revolution trajectories between noncoplanar elliptical and circular orbits with a free apse line of the initial orbit. These features allow us to compute universal tables of the characteristic velocity and initial values of conjugate variables. A formulation of suboptimal feedback control based on the use of these universal tables is given. The description of the method of using universal tables of characteristic velocity for designing trajectories of spacecraft insertion into a high circular final orbit with sequential use of high and low thrust engines is given. Numerical examples of application of suboptimal feedback control for calculation of low-thrust trajectories to the Moon and libration points of the Earth-Moon and Earth-Sun systems are presented.