Attitude control of asymmetric spacecrafts subject to actuator failures

This paper provides a solution to the problem of controlling the orientation of a geostationary spacecraft, subject to actuator failures. The proposed scheme is based on a two levels Supervisory Switching Logic. It selects the most appropriate controller from a bank of candidate control laws, depending on the state of the actuators. In order to establish the working conditions of the satellite, techniques of fault detection and fault diagnosis are adopted.