Spacecraft quaternion based attitude input-output feedback linearization control using reaction wheels

The aim of this paper is attitude control of spacecraft utilizing nonlinear control feedback linearization. Input-output linearization is a technique of feedback linearization theory. In this method choosing of output functions is very important and has a direct effect on stability. Here state variables are selected as output functions. In order to make sure that internal dynamic is stable and performance of controller is acceptable, zero dynamics analysis has handled. Optimal torque of each reaction wheel is determined based on distribution matrix of configuration and torque magnitude optimization of actuators. The simulation results show that the method has been successful to control the attitude of spacecraft.