Multi-Objective Control of Spacecraft Attitude Maneuver Based on Takagi-Sugeno Fuzzy Model

Abstract

The multi-objective control for a rigid spacecraft maneuver is designed in this paper, which contains disturbances rejection, decay rate, and input constraint. Firstly, the rigid spacecraft model consisting of the dynamic and kinematics equation are provided. This nonlinear system is converted into a Takagi-Sugeno fuzzy model. And based on the parallel distributed compensation (PDC) scheme, a fuzzy state feedback controller is designed, which guarantees the closed-loop system to meet the multi-objective design requirements. Furthermore, the problem is reduced to a convex optimization involving linear matrix inequalities (LMIs). The simulation results demonstrate that the proposed controller can guarantee the stability of control system and good disturbance attenuation.