One de-orbit attitude control system coupled with liquid sloshing of residual fuel

This paper studies attitude control problem of a rocket during de-orbiting experiment. The attitude maneuver process may fail due to the disturbance of liquid sloshing of residual fuel. The problem of fluxion and liquid sloshing are frequently met in practical projects, which calls for relatively large computing resources. The torque judgment pattern of system with respect to liquid sloshing is built in this paper, which offers significant economy of computing and focuses more on the attitude dynamics of the integrated system. The general purpose is to present a critical control mode that minimizes the change of the initial design by investigating the ability of the torque judgment pattern and analyzing the essential features for attitude stabilization control system.