अमूर्त

Artificial Neural Networks based Attitude Controlling of Longitudinal Autopilot for General Aviation Aircraft

Nagababu V, Imran A

Generally, Aircraft fly in three axes plane by controlling aileron, rudder and elevator. They are designed to change and control the moments about the roll, pitch and yaw axes. The control system of the aircraft is divided into two portions, longitudinal and lateral control. In longitudinal control, the elevator controls pitch or the longitudinal motion of aircraft system. The pitch of aircraft is control by elevator which usually situated at the rear of the airplane running parallel to the wing that houses the ailerons. PID controllers are commonly used in many control systems because of their simple structures and intuitionally comprehensible control algorithms. But these methods are poor at disturbance rejection. In this paper ANN-PID (Artificial Neural Networks-Proportional Integral Derivative) controller is introduced, taking the advantages of PID controller. The performance of control schemes, PID and ANN-PID controllers with respect to the pitch angle of aircraft longitudinal dynamics are investigated by applying different disturbances like step, sinusoidal, band limited white noise, Repeating Sequence, Chirp signal. Simulation is developed within Simulink and MATLAB (Matrix laboratory) for evaluation of the control strategies.