| Modified Non-linear PID Controller Design for Small UAV |
| Paper ID : 1182-IUGRC5 |
| Authors: |
|
Ahmed Kamel *1, Ehab Khattab2, Samy Samir Mohamed2, Ahmed Mohamed Elshahat2, Nader Ashraf1 1Guidance Department 2Naval Armament |
| Abstract: |
| Fixed-wing unmanned aerial vehicles (UAVs) have become increasingly important in military, civil, and scientific sectors. Because of the existing nonlinearities, effective control this type of UAV remains a challenge. This paper proposes a modified proportional-integral derivative (PI-D) control system for fixed-wing UAVs where a family of PID cascade control systems is designed for several operating conditions of airspeed. The proposed modification of the PID controller based on adopting the angular rates measured by the angular gyroscopes as negative feedback instead of differentiating the desired step reference. The practical enhancement ensured from this modification due to the validity of the Inertial Measuring Unit (IMU) sensors to provide the required feedback; where the IMU three gyroscopes provide the vehicle angular rates, and the IMU three accelerometers provide the vehicle linear acceleration. Moreover, the anti-windup mitigation introduced by preventing background integration while saturation. The numerical simulation results confirm the reduction of the control effort using the proposed modifications. |
| Keywords: |
| PI-D, UAV, Set-point Kick, anti-windup. |
| Status : Paper Accepted (Oral Presentation) |
