On Designing Fault Estimator for Satellite Attitude Control System with Typical Component Configuration

This paper deals with the problem of fault estimation for satellite attitude control system with typical component configuration. In order to understand sensor and actuator faults propagation in the attitude control system, we have built the overall system model firstly, which includes the attitude dynamics model, sensor measurement model, attitude determination model, controller model and the moment distribution model. The faults are then considered as unknown inputs and are estimated using a classical proportional-integral observer, more over constant or time-varying fault can be estimated. The proposed observer is derived as a solution of off-line Linear Matrix Inequality (LMI) conditions. Additionally, simulation results are presented to illustrate the efficiency of the proposed method.