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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.
Aiming at spacecraft attitude stability control system with parameter uncertainties, a class of finite-time attitude controller based on odd-order theory is proposed.Firstly, by introducing a new adaptive state variable, the spacecraft attitude control system is converted into a Then, based on the theory of homogeneousness, a new class of asymptotically stable controllers for finite time is designed. By using Lyapunov theory, the asymptotic behavior of the system in the presence of parametric uncertainties is proved Stability and the finite-time stability of the closed-loop system in the absence of parametric uncertainty.Finally, the proposed algorithm is applied to the attitude stabilization of a rigid-body spacecraft. The numerical simulation results verify the effectiveness and feasibility of the proposed scheme.