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We investigate solar sail in the circular restricted three-body problem, where the larger primary is a source of radiation and the smaller primary is an oblate spheroid in the system. Firstly, the differential equations of motion for solar sail in the system combined effects of radiation and oblateness of celestial bodies are built. Then the positions of the solar sail collinear Lagrange points are calculated as mass ratio or oblateness changes in certain extent. Linearization near the collinear equilibria of the system is applied. A linear quadratic regulator is used to stabilize the nonlinear system. Three different cases of solar sail equilibrium orbits are studied each with different choices for the weight matrices. The simulations reveal that solar sail equilibrium orbits can be stable under active control by changing three angles, incident angle, cone angle and clock angle of the solar sail.

Solar Sail Equilibrium Orbits in the Circular Restricted Three-Body Problem with Oblateness