Application of fault diagnosis on satellite attitude control system using multiple frequency H∞ observers

In order to do gyro fault diagnosis for satellite attitude control system, a series of multiple frequency H∞ optimal fault observers are designed using LMI based on input information and the different frequencies of the faults. This method does not require other measured rectification. Thus the diagnosis can be independent of star sensors. Also, it extends a design freedom such that the H∞ observers can mitigate the impact on the diangosis caused by inertial uncertainty. In the study, a simulation on spacecraft attitude system is conducted using Matlab/Simulink softwares. The simulated results demonstrate the effectiveness and feasibility of the proposed control algorithm.