In this paper, a novel finite time suboptimal control design method (named ϴ − D technique) to two spacecraft Coulomb formation at the Earth-Moon libration points is investigated. By employing this proposed technique, the relative distance between them can be driven to a desired value at a finite time from the initial positions. Meanwhile, three nonlinear dynamic configurations to two spacecraft Coulomb formation are considered in this study, which are orbit radial direction configuration, along track direction configuration and orbit normal direction configuration. Finally, the effectiveness of the proposed control design technique is demonstrated by the numerical simulations, indicating potential of this proposed technique to this formation control application and to other engineering applications.