Abstract
The design of a robust and fault-tolerant control system for the attitude control of a satellite launch vehicle is described. The robust controller is designed for the nominal system in order to reduce the effect of disturbances in the system. Finally, a reconfigured controller is designed to stabilise the system by placing the closed-loop poles within a desired region and also to guarantee the disturbance attenuation below a certain level. The linear matrix inequality technique is used to design the controllers. The performance of the nominal and reconfigured controller is presented.
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