A reliable nacelle decoupling mechanism control effect can be achieved while using the embedded computer PC/104 actualized closed loop control system. It also obtained a continuous control,high precision and reliability when combining with reaction flywheel control system.
This paper introduced the structure of a permanent magnet bias magnetic bearing reaction flywheel for stabilization of spacecraft attitude. Its rotation speed is from-5000rpm to 5000rpm(rating angular momentum is 50Nms).
The simulation proved that the Instrument-in-Loop method can greatly improve the precision of attitude determination with low cost. The small astronomical satellite has demands on both pointing accuracy and attitude maneuverability, so this thesis modeled the attitude control subsystem based on reaction wheels.
The quaternion feedback control laws was studied for the three-axis stabilization control using reaction wheels, a design method for the PID controller parameters was presented and the simulation results indicated that the control algorithm works efficiently.