Fuzzy Sliding Mode Control of a Spacecraft Attitude Tracking System

摘要：

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.

作者: Guangfu MA Bin SONG Chuanjiang LI

作者单位: Harbin Institute of Technology, China

会议类型: 国际会议

会议名称: 2nd IEEE Conference on Industrial Electronics and Applications(ICIEA 2007)(第二届IEEE工业电子与应用国际会议)

会议地点: 哈尔滨

会议语种:英文

在线出版日期: 2007-05-23（万方平台首次上网日期，不代表论文的发表时间）