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This paper proposes a gyro and star sensor fault diagnosis architecture that designs two groups of cascade H∞ optimal fault observers using LMI for spacecraft attitude control systems and schemes a Compensation PD controller to achieve fault tolerant control. The basic idea of the approach is to identify the gyro fault to good effect first and then makes a further diagnosis for the star sensor based on the former. The H∞ optimal fault observers in design have the robustness with respect to model uncertainties, disturbance and diagnosis uncertainties. The Compensation PD controller ensures the attitude error maintains to a small set around the equilibrium point even though the gyro and star sensor faults occur simultaneously. Simulation results demonstrate the effectiveness and feasibility of the proposed control algorithm.
Date of Conference: 15-17 June 2010