具有参数不确定性的航天器姿态有限时间稳定控制

Finite-time Spacecraft Attitude Stabilization Control Subject to Parameter Uncertainties

针对存在参数不确定性的航天器姿态稳定控制系统,提出了一类基于奇次性理论的有限时间姿态控制器.首先,通过引入新的自适应状态变量,将航天器姿态控制系统转换为一个级联系统;然后,基于齐次性的理论方法,设计了一类新颖的有限时间渐近渐近稳定控制器,并利用李亚普诺夫理论,证明了系统在存在参数不确定性时的渐近稳定性及不存在参数不确定性时的闭环系统有限时间稳定性.最后,将提出的算法应用于某刚体航天器姿态稳定控制任务中,数字仿真结果验证了方案的有效性和可行性.

We propose a novel, finite-time control scheme based on the homogeneous method for a rigid spacecraft with parameter uncertainties and external disturbances. First, the spacecraft attitude control system is transformed into a cascading system by introducing an adaptive variable. Second, we propose a novel control scheme of finite-time attitude stabilization for the rigid spacecraft based on the homogeneous method. Next, we prove the asymptotic stability of the system with parameter uncertainties and finite-time stability of the closed-loop system without parameter uncertainties based on Lyapunov theory. Finally, the proposed algorithm is demonstrated on a rigid spacecraft attitude stabilization control mission, and the digit simulation demonstrates that the control strategy is feasible and effective.