This chapter investigates the problem of coupled orbit-attitude control for solar sail formation flying where the leader follows a solar-sail resonant halo orbit in the Earth-Moon Circular Restricted Three Body Problem, whereas the follower is controlled to track a predefined reference relative trajectory around the leader. Taking the reflectivity control devices (RCD) as joined orbit and attitude control actuators, their force and torque models are first established for a spinning solar sail. In particular, the saturation and coupling of the control variables for the coupled orbit-attitude control are focused.