This work presents a novel approach for the attitude control of spacecraft during the de-orbit process. It implements the fluidic rings as the momentum exchange device to stabilize the orientation of spinning axis and damp the disturbance torque of liquid sloshing and environmental disturbances. Fluidic rings utilize the residual fuel in the tank and accelerate them in the rings by the pump to produce the required torque. The dynamics of a vehicle with three fluid rings is developed first. The influence of the liquid sloshing is incorporated by the computational fluid dynamics (CFD) method. Then, a control law is designed by Lyapunov method. Numerical simulations are given to demonstrate the effectiveness of the proposed control schemes.
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