In this paper two strategies are described for attitude control for Unmanned Aerial Vehicle (UAV) of type quadrotor aircraft. One strategy is based on the classical PID control (Proportional - Integral - Derivative) and other on a fuzzy logic control. Both controls were modeled, implemented and simulated in Matlab/Simulink. The simulation results and the comparison of both controllers are presented and discussed. Also we analyzed the behavior of the both controllers in the presence of disturbances. The fuzzy controller showed better results than the PID.