考虑控制输入受限的卫星姿态控制

Satellite attitude control subject to control input constraints

研究了刚体卫星在控制输入受限时的姿态调节控制问题.设计了基于饱和函数的非线性控制器,在控制输入受限的同时,也是角速度受限的.通过李亚普诺夫方法证明了闭环系统零平衡点的全局渐近稳定性,保证了姿态和角速度都是渐近趋于零的.所提出的控制方案是模型独立的,不依赖于卫星的转动惯量.仿真结果表明,在控制输入受限情况下,用所设计的控制方案实现姿态控制是可行的、有效的.

This paper deals with the problem of attitude regulation control of rigid satellite subject to control input constraints.A nonlinear controller based on the saturation function is designed to deal with the control input saturation and angular velocity constraint.Lyapunov theory is employed to prove the global asymptotic stability of the zero equilibrium points of the closed loop system and both attitude and angular velocity will tend to be zero asymptotically.The controller is derived independent of satellite inertia matrix,and the control scheme is model independent.Simulation results demonstrate the feasibility and effectiveness of the control scheme under control input constraints.