1Modelling the Aircraft and Actuator DynamicsaNormal Acceleration The acceleration of the aircraft in a direction perpendicular to its axis the normal accel is determined mainly by the angle of the

PID parameters used: Proportional gain (Kp) = 1.5 Integral gain (Ki) = 2 Derivative gain (Kd) = 0.1

The best response obtained had less than 5% overshoot and steady-state error = 0. The PID controller was able to quickly respond to changes in the input and stabilize the pitch rate of the aircraft. The proportional gain (Kp) was set to a higher value to provide a faster initial response, while the integral gain (Ki) was set to a moderate value to eliminate steady-state error. The derivative gain (Kd) was set to a small value to dampen oscillations and provide a smoother response. Overall, the PID controller was able to significantly improve the control performance compared to the proportional controller used previously