Dynamic inversion control of liquid-filled spacecraft attitude and fuel sloshing suppression

Input shaping technique was applied to fuel sloshing suppression induced by the duration of attitude maneuver. A Single pendulum model of liquid-filled spacecraft was built, whose dynamical coupled equations were deduced, and a nonlinear dynamic inversion control also established. The ZVD input shaper was designed basing on the frequency and damping of fuel sloshing. The lows between preset controlling system ZVD input shaper and shaping of input commands were revealed. At the end of this paper, the results of numerical simulation were used to verify the effectiveness of attitude stabilization of spacecraft when using the new controlling system.