TY - GEN
T1 - Performance analysis of a tiltrotor UAV flight stability using PID controller
AU - Hegde, Navya Thirumaleshwar
AU - George, V. I.
AU - Nayak, C. Gurudas
N1 - Publisher Copyright:
© Springer Nature Singapore Pte Ltd. 2020.
PY - 2020
Y1 - 2020
N2 - This research paper presents an improved proportional–integral–derivative (PID) controller for six-degrees-of-freedom (DOF) unmanned aerial vehicle (UAV) flight stability control. Quad tiltrotor hybrid UAV exhibits particular application value because of its distinctive structure of rotors. Variation in the model dynamics and aerodynamics due to the tiltrotor feature is a great technical challenge and critical issue which has fascinated many researchers in this area. The capability of an airplane to cruise at high speed as well as the distinct feature of hovering in helicopters can be merged as a result of tilting the quadruple rotors of the UAV. Transition refers to the altering between hover and cruise flight modes in mid-air. The mathematical model is developed for both horizontal and vertical flight modes using Newton–Euler formulation. The attitude, as well as the altitude of the UAV, is stabilized through a PID control approach. The results of simulation depict that the presented controller succeeds in achieving good adaptability, robust stability, as well as performance in all three flight modes.
AB - This research paper presents an improved proportional–integral–derivative (PID) controller for six-degrees-of-freedom (DOF) unmanned aerial vehicle (UAV) flight stability control. Quad tiltrotor hybrid UAV exhibits particular application value because of its distinctive structure of rotors. Variation in the model dynamics and aerodynamics due to the tiltrotor feature is a great technical challenge and critical issue which has fascinated many researchers in this area. The capability of an airplane to cruise at high speed as well as the distinct feature of hovering in helicopters can be merged as a result of tilting the quadruple rotors of the UAV. Transition refers to the altering between hover and cruise flight modes in mid-air. The mathematical model is developed for both horizontal and vertical flight modes using Newton–Euler formulation. The attitude, as well as the altitude of the UAV, is stabilized through a PID control approach. The results of simulation depict that the presented controller succeeds in achieving good adaptability, robust stability, as well as performance in all three flight modes.
UR - https://www.scopus.com/pages/publications/85088750386
UR - https://www.scopus.com/pages/publications/85088750386#tab=citedBy
U2 - 10.1007/978-981-15-4676-1_22
DO - 10.1007/978-981-15-4676-1_22
M3 - Conference contribution
AN - SCOPUS:85088750386
SN - 9789811546754
T3 - Lecture Notes in Electrical Engineering
SP - 241
EP - 251
BT - Advances in Control Instrumentation Systems - Select Proceedings of CISCON 2019
A2 - George, V.I.
A2 - Roy, B.K.
PB - Springer Gabler
T2 - 16th Control Instrumentation System Conference, CISCON 2019
Y2 - 8 November 2019 through 9 November 2019
ER -