摘要
针对带不确定项的空间飞行器系统姿态跟踪控制问题,给出一种基于有限时间控制技术的滑模控制方法。使得姿态跟踪误差系统不仅可在有限时间内从任意状态到达滑动面,而且也可在有限时间内沿滑动面收敛到零,并给出了严格的数学证明。为了避免控制律中的颤动问题,一种新的饱和函数被用来代替控制律中符号函数。数值仿真实验说明了该方法的有效性。
A sliding mode control method based on finite-time control technology is designed for the spacecraft attitude tracking control system in the presence of uncertain term. The tracking error system can not only be controlled to the sliding manifold from any initial state in finite-time but also converge to zero along the sliding manifold in finite-time, Rigorous mathematical proof is also given. In order to avoid the chattering problem, the sign function in control law is substituted by a new saturation function. Numerical simulation results are presented to validate the effectiveness of the system.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2007年第3期628-633,共6页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(60504007)
东南大学优秀青年教师资助项目
关键词
姿态控制
有限时间收敛
滑模控制
空间飞行器
attitude control
finite-time convergence
sliding mode control
spacecraft
