In this thesis, the attitude control schemes of pulse modulated flexible spacecraft are studied. This study starts from classical methods and show the difficulty of control of flexible spacecraft equiped with gas jet thruster due to the interaction between nonlinearities of pulse modulator and flexible modes of spacecraft.
Also the $H_\infty$ controller is designed for that spacecraft and finally a new method using fuzzy control scheme is proposed. New scheme is composed of scaling factor adaptation and varying membership function variables. The simulation results are given to verify the advantage of new method.
