The variable structure control of spacecraft during spring-eject separation

This paper aims to the control problems of spacecraft when a small flyer separated from a main spacecraft in orbit. Firstly, the kinetic model is established and disturbance of spring-eject separation on the main spacecraft is analyzed. Secondly, we choose the variable structure control method to control the main spacecraft attitude because the whole system is complex nonlinear coupling system during separation. Concretely, we design sliding mode control law to solve this problem through choosing reasonable sliding surface and its update law. Finally, simulation results indicate the validity of the designed sliding mode control law.