Fuzzy Control of satellite Attitude Maneuver based on T-S Model
This paper presents a Takagi-Sugeno (T-S) model based fuzzy control design approach for rigid satellite attitude maneuver. The T-S fuzzy model is first applied to represent the rigid satellite model consists of dynamic and kinematics equation. Then, a fuzzy state feedback controller is designed for the obtained T-S fuzzy model with considering the decay rate by using the parallel distributed compensation scheme. Then, sufficient conditions for the existence of such a controller are derived in terms of linear matrix inequalities (LMIs) and the controller design is cast into a convex optimization problem subject to LMI constraints, which can be readily solved by Matlab. The mathematical simulation results of example show that the time of satellite maneuver is shortened.
attitude control Takagi-Sugeno model nonlinear dynamic system linear matrix inequalities decay rate
Ming Zeng Xihai Zhang
Space Control and Inertial Technology Research CenterHarbin Institute of TechnologyHarbin, China Space Control and Inertial Technology Research Center Harbin Institute of Technology Harbin, China
国际会议
成都
英文
1-4
2010-08-20（万方平台首次上网日期，不代表论文的发表时间）