Anti-windup Design for Satellite Control with Microthrusters

Future space missions (e.g. microscope, formation flying, rendez-vous) demand for an acceleration or relative position control. That requires actuators that can provide an effort in the linear axis. Therefore propulsion systems apply. Then, these same systems are used for the attitude control instead of the reaction wheels. At the same time a high precision is demanded. Thus microthrusters are needed as they are able to perform an almostcontinuous propulsion, between zero and its maximum, with a quantization. Even though they satisfy the demands on high precision, the maximal propulsion capacity appears to be critically low, which could lead to the saturation of the actuator. A model of the systems needing longitudinal efforts with high precision is presented. Microthrusters used in these kind of systems are also characterized. An anti-windup controller design technique is proposed for this kind of actuators. Simulations consider the attitude control of an axis of a satellite. They show how the anti-windup controller increases the level of saturation allowed as well as the disturbance amplitude. Simulations are based on a nominal model provided by CNES and developed in matlab/simulink.

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