基于会切场推力器的无拖曳控制系统建模

In order to study the modeling method of drag-free control system of spacecraft and assess the effects of cusped field thruster performance and sensor measurement errors on control system performance, a drag-free control system is designed based on orbit dynamic theory, atmospheric drag model, PID control method and the experimental data of the cusped field thruster. Furthermore, the effects of thrust resolution, transient response time of thruster and sensor measurement errors on closed loop system are analyzed. The simulation results show that the control system has good performance and thrust resolution and sensor errors have slight influence on the overall system. But thruster response delay has a greater impact on control system precision, which needs further optimization in later studies. Considering the above factors, the maximum displacement error of closed loop system in the spacecraft velocity direction is 747.51nm, the maximum velocity error is 733.36nm/s. The simulation results show the application feasibility of cusp field thruster in drag-free missions.