A study about instrument fault detection and analytical redundancy applied to a satellite launcher flight control system

A study on the inclusion of analytical redundancy and an instrument fault detection scheme into a flight control system has been performed for a satellite launcher. Fault diagnosis logic has been created based on nonlinear functions, its time derivatives, and on the control rate effort. The robustness of the system with respect to system parameters was studied. Safe control law reconfiguration is possible in almost all cases. The false alarm rate presented was very low. The same observers are used for the decision logic and for the alternative observer-based control laws.