TY - GEN
T1 - Application of Unmanned Aircraft PID Control System for Roll, Pitch and Yaw Stability on Fixed Wings
AU - Susanto, Try
AU - Setiawan, Muhammad Bayu
AU - Jayadi, Akhmad
AU - Rossi, Farli
AU - Hamdhi, Afrizal
AU - Persada Sembiring, Jaka
N1 - Publisher Copyright:
© 2021 IEEE.
PY - 2021
Y1 - 2021
N2 - 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.
AB - 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.
KW - Fixed Wings
KW - PID
KW - Unmanned Aerial Vehicle
UR - http://www.scopus.com/inward/record.url?scp=85124339427&partnerID=8YFLogxK
U2 - 10.1109/ICOMITEE53461.2021.9650314
DO - 10.1109/ICOMITEE53461.2021.9650314
M3 - Conference contribution
AN - SCOPUS:85124339427
T3 - 2021 International Conference on Computer Science, Information Technology, and Electrical Engineering, ICOMITEE 2021
SP - 186
EP - 190
BT - 2021 International Conference on Computer Science, Information Technology, and Electrical Engineering, ICOMITEE 2021
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2021 International Conference on Computer Science, Information Technology, and Electrical Engineering, ICOMITEE 2021
Y2 - 27 October 2021 through 28 October 2021
ER -