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.
Robust and fault tolerant controller for attitude control of a satellite launch vehicle
IET Control Theory and Applications ; 1 , 1 ; 304-312
2007
9 Seiten, 29 Quellen
Aufsatz (Zeitschrift)
Englisch
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