Application of Unmanned Aircraft PID Control System for Roll, Pitch and Yaw Stability on Fixed Wings

Unmanned Aerial Vehicle (UAV) is an unmanned aircraft currently undergoing many developments in the non- military or military field, which is widely used to assist human work in mapping missions of a region until it is used as a military weapon. UAVs have two types of wing types: Fixed-wing UAV, a vehicle that requires an airstrip to perform a take-off, and Rotary-wing UAV, which has rotating wings for performing vertical take-off. The flying mode on the UAV itself can be controlled in 2 ways: manually and automatic flying controlled by a system embedded in the aircraft. Some problems or disturbances occur when the aircraft is maneuvering in the air; one is the loss of stability. The study proposes a PID method overcoming the loss of stability on the flying aircraft. The method is a combination of 3 controls: Proportional Control, Integral Control, and Derivative Control. The result shows that the PID method has been successfully applied to fixed-wing vehicles and can control the stability of the roll, pitch, and yaw angles when flying independently.