论文标题
刚性航天器的滑动模式态度操纵控制而无需放松
Sliding Mode Attitude Maneuver Control for Rigid Spacecraft without Unwinding
论文作者
论文摘要
在本文中，对刚性航天器进行了研究，而没有放松现象的态度操纵控制。首先，通过双曲线正弦函数构建新颖的切换函数。结果表明，当系统状态在滑动表面上时，航天器系统具有无松散的性能。基于设计的开关函数，开发了滑动模式控制器，以确保态度操纵控制系统的鲁棒性。提出的态度控制定律的另一个基本特征是，引入了动态参数，以确保当系统状态在滑动表面之外时，无效的性能。模拟结果表明，通过采用构造的开关函数和提议的态度控制方案，避免了在刚性航天器的态度操纵期间避免放松现象。
In this paper, attitude maneuver control without unwinding phenomenon is investigated for rigid spacecraft. First, a novel switching function is constructed by a hyperbolic sine function. It is shown that the spacecraft system possesses the unwinding-free performance when the system states are on the sliding surface. Based on the designed switching function, a sliding mode controller is developed to ensure the robustness of the attitude maneuver control system. Another essential feature of the presented attitude control law is that a dynamic parameter is introduced to guarantee the unwinding-free performance when the system states are outside the sliding surface. The simulation results demonstrate that the unwinding phenomenon is avoided during the attitude maneuver of a rigid spacecraft by adopting the constructed switching function and the proposed attitude control scheme.
