Fault tolerant controller for attitude control of satellite launch vehicle via LMI approach

This paper addresses the design methodology of a fault tolerant controller for the attitude control of satellite launch vehicle. A fault detection technique using parity space approach has been employed to detect the single actuator fault. The LMI technique has been used to design the controllers (both nominal and reconfigured) to stabilize the system by placing the closed loop poles within a desired region and also to guarantee the disturbance attenuation below a certain level. The performances of the fault tolerant controller have been presented in this paper.