充液飞行器大角度操纵变结构控制

VARIABLE-STRUCTURE CONTROL OF LIQUID-FILLED SPACECRAFT LARGE-ANGLE MANEUVERS

本文利用交结构控制理论的原理研究了全充液飞行器的大角度操纵问题。基于充液飞行器的简化模型,在状态空间中设计控制规律以约束状态至滑模。滑模通过在一个约化空间中求解最优控制问题获得,其解是角速度作为姿态变量的函数。算例显示沿着滑模的运动对参数变化与非模型效果不敏感。

The liquid-filled spacecraft large-angle maneuver problem is investigated using the principles of variable-structure control theory. A control law, that constrains the state to follow the sliding mode in the state space, is designed on the basis of a nonlinear, simplified model of the completely liquid-filled spacecraft dynamics. The sliding mode is obtained by solving an optimal control problem posed in a reduced space, the solution being the angular velocities of the spacecraft as functions of the attitude variables. It is shown that the motion along the sliding mode is insensitive to parameter variations and unmodeled effects.