This paper presents microsatellite yaw-axis attitude control using Fuzzy Logic Control system. The mathematical models of amplifier, actuator, and satellite structure for determining the transfer function a microsatellite yaw-axis attitude were obtained. A FLC algorithm was developed. A MATLAB/Simulink model, which was computer-based model, was developed using the mathematical models of the closed control system. The FLC was introduced into the system, which resulted in settling time 4.29 s and zero overshoot, indicating the capacity to offer smooth transient response.