In the formation flying mission, the periodic revisit of multiple formation satellites can provide periodic surveillance of satellite status, e.g., on-orbit inspection. This paper studies the orbit design problem and the single-impulse control problem for periodically revisiting multiple formation satellites. Two periodic revisit conditions under the J2 perturbation are considered: the J2 invariant orbit and the same mean semi-major axis. By analyzing the numbers of free variables and constraint equations, the maximum numbers of revisiting satellites are obtained for both the coplanar and non-coplanar cases. A hybrid method is proposed by combining the state transition matrix and the second-order state transition tensor, which are used to solve the required velocity vector and to propagate the relative state vector, respectively. The original multi-dimensional nonlinear equation is reduced into a one- or two-dimensional equation, which is solved by numerical methods. Several numerical examples show that the revisit orbit drifts after 30 revolutions by the proposed method for the coplanar and non-coplanar cases are less than 0.3 km and 4.5 km, respectively.