论文标题
防波子滑动模式态度态度控制刚有航天器的操纵控制
Anti-Unwinding Sliding Mode Attitude Maneuver Control for Rigid Spacecraft
论文作者
论文摘要
在本文中，考虑了对刚性航天器的反风态度操纵控制。首先，为了避免系统状态仅限于开关表面时的放松现象，通过双曲线正弦函数构建了新颖的开关函数，以使开关表面包含两个平衡。然后，基于构造的开关功能设计了滑动模式态度操纵控制器，以确保闭环态度操纵控制系统的鲁棒性对干扰。开发的态度控制定律的另一个重要特征是引入动态参数，以确保系统状态到达开关表面之前的反风能。仿真结果表明，在态度操作期间，通过采用新建造的切换功能和拟议的态度控制方案来解决僵化航天器的态度操作。
In this paper, anti-unwinding attitude maneuver control for rigid spacecraft is considered. First, in order to avoid the unwinding phenomenon when the system states are restricted to the switching surface, a novel switching function is constructed by hyperbolic sine functions such that the switching surface contains two equilibriums. Then, a sliding mode attitude maneuver controller is designed based on the constructed switching function to ensure the robustness of the closed-loop attitude maneuver control system to disturbance. Another important feature of the developed attitude control law is that a dynamic parameter is introduced to guarantee the anti-unwinding performance before the system states reach the switching surface. The simulation results demonstrate that the unwinding problem is settled during attitude maneuver for rigid spacecraft by adopting the newly constructed switching function and proposed attitude control scheme.
