Abstract: In order to solve debris removal problem, a capture method of mixed formation of spacecraft and space debris is proposed. Firstly, the restricted three-body circumstance near the L₂ point of Earth/Moon-Sun is analyzed and the relative dynamics model of formation satellites is established. Then, a control strategy, using sunlight pressure as the spacecraft and debris formation reconfiguration force, is proposed so that achieving the purpose of approaching debris by follower satellites. Lastly, a linear quadratic optimal controller is designed and simulated by Matlab/Simulink. The results show that the method can help control followers achieve the target track (location of space debris), while the change of the solar sail attitude is kept under control. Therefore, it proves that the method can applied to the debris removal problem in complex space environment.