We investigate solar sail displaced orbits in the Hill’s restricted three-body problem was investigated, where the larger primary was an oblate spheroid in the system. Firstly, the model of solar sail equipped with a new version of reflectance control device was introduced. Next, dynamical model of the system with the larger primary an oblate spheroid was established and the Hill’s restricted three-body problem with oblateness was built through appropriate simplifications. The collinear equilibrium points of the Hill’s system varying with the variations of areas of absorption and thermal radiation of reflectance control devices in the solar sail, or the dimensionless characteristic acceleration of solar sail, or the oblateness of the larger primary are also investigated. Then, Linearization near the collinear equilibria of the system is applied. A linear quadratic regulator was used to stabilize the nonlinear system. The simulation reveals that solar sail displaced orbits in this system are doable and asymptotically stable by means of adjusting the pitch angle of solar sail and the area of absorption in reflectance control devices.