Fuzzy Sliding Mode Control of a Spacecraft Attitude Tracking System
Fuzzy Sliding Mode Control of a Spacecraft Attitude Tracking System
复制标题
航天器姿态跟踪系统的模糊滑模控制
DOI：
10.1109/iciea.2007.4318699
复制
发表时间：
2007
期刊：
影响因子：
--
通讯作者：
C.J. Li
中科院分区：
文献类型：
--
作者：
G. Ma;B. Song;C.J. Li
研究了具有不确定惯性矩阵和外部干扰的刚体航天器姿态跟踪控制问题。提出了一种基于相对运动学和动力学方程的模糊滑模控制方法。利用相对姿态运动学和动力学方程构造控制律的优点是可以将跟踪控制问题转化为调节控制问题，简化了设计问题。该控制方案集成了模糊逻辑和滑模控制，并利用模糊逻辑在一个薄边界层内平滑控制间断，从而消除了滑模控制系统中的抖振现象。数值仿真结果证明了所提出的控制方案的有效性。
The main problem addressed is attitude tracking control of a rigid spacecraft with uncertain inertia matrix and external disturbances. A fuzzy sliding mode control approach is presented based on relative kinematics and dynamics equations. The advantage of using relative attitude kinematics and dynamics equations to construct control law is that it can convert tracking control problem into regulation control problem, which simplifies the design problem. The control scheme integrates the fuzzy logic and the sliding mode control, and the control discontinuity is smoothed inside a thin boundary layer using the fuzzy logic so that the chattering phenomenon in a sliding mode control system is eliminated. Numerical simulations are included to demonstrate the effectiveness of the proposed control scheme.