Research On Spacecraft Attitude Control Based On Fuzzy Sliding Mode Variable Structure Control

The conventional design of attitude control system is complicated and inefficient due to the large-bound changes of parameters of the space vehicle model during flying. First the fundamental of sliding mode variable structure control and the aerocraft attitude control system are introduced. Second two kinds of design methods which respectively based on sliding mode variable structure control and fuzzy control are put forward. From comparison, one can conclude that the robust performance of fuzzy sliding mode variable structure control is much better. Finally, according to the model data of a spacecraft attitude control system of the mathematical simulation, simulation results shows that fuzzy sliding mode variable structure control can effectively control the state of aerocraft whose dynamic parameters are time-varying and uncertain. Therefore, fuzzy sliding mode variable structure control using this method can stabilize the aerocraft and effectively reduce the attitude angle error. As the design of both the controller and the method is simple and can be realized easily, it is a more efficient engineering method of practical value.