Applied and Computational Engineering

- The Open Access Proceedings Series for Conferences


Proceedings of the 2023 International Conference on Mechatronics and Smart Systems

Series Vol. 9 , 25 September 2023


Open Access | Article

Controller design for transition flight of rotor-driven VTOL fixed-wing UAV based on PID

Kaixiang Chen * 1
1 Chongqing University

* Author to whom correspondence should be addressed.

Applied and Computational Engineering, Vol. 9, 15-21
Published 25 September 2023. © 25 September 2023 The Author(s). Published by EWA Publishing
This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
Citation Kaixiang Chen. Controller design for transition flight of rotor-driven VTOL fixed-wing UAV based on PID. ACE (2023) Vol. 9: 15-21. DOI: 10.54254/2755-2721/9/20230018.

Abstract

The field of drones has received a lot of attention in recent years and is developing well. In the process of resource circulation in cities, UAVs play an increasingly important role, such as logistics, monitoring, emergency rescue, etc. However, traditional rotary-wing UAVs and fixed-wing UAVs can be limited in some conditions, such as load, cruising speed and take-off area. Based on the above reasons, this paper designs a rotor-driven VTOL fixed-wing UAV, which combines the vertical take-off and landing of rotor and the fast cruise of fixed-wing UAV and other characteristics. And based on this UAV, for the transition process from hovering state to cruising state, a PID controller is used to control the cruising speed, and then the flight altitude is controlled by a series-level PID controller. The final results show that the cruise speed can be stabilized at about 50km/h within 3 seconds by adjusting the PID parameters without considering the motor speed saturation. In addition, while ensuring the cruise speed reaches convergence quickly, the PID parameters of the acceleration loop, velocity loop and altitude loop can be adjusted separately to control the altitude error of the UAV within 5cm. This study provides a reference for researchers to study the control of rotor-driven UAVs in the transition process.

Keywords

PID, rotor-driven VTOL fixed-wing UAV, transition process, cruise speed control, altitude control.

References

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Data Availability

The datasets used and/or analyzed during the current study will be available from the authors upon reasonable request.

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Volume Title
Proceedings of the 2023 International Conference on Mechatronics and Smart Systems
ISBN (Print)
978-1-83558-007-3
ISBN (Online)
978-1-83558-008-0
Published Date
25 September 2023
Series
Applied and Computational Engineering
ISSN (Print)
2755-2721
ISSN (Online)
2755-273X
DOI
10.54254/2755-2721/9/20230018
Copyright
25 September 2023
Open Access
This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited

Copyright © 2023 EWA Publishing. Unless Otherwise Stated