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Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft

Xufei YAN Orcid Logo, Ye Yuan, Yanqin ZHAO Orcid Logo, Renliang CHEN

Chinese Journal of Aeronautics, Volume: 37, Issue: 3, Pages: 153 - 167

Swansea University Author: Ye Yuan

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DOI (Published version): 10.1016/j.cja.2023.09.016

Abstract

Manned multi-rotor electric Vertical Takeoff and Landing (eVTOL) aircraft is prone to actuator saturation due to its weak yaw control efficiency. To address this inherent problem, a rotor cross-tilt configuration is applied in this paper, with an optimization method proposed to improve the overall c...

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Published in: Chinese Journal of Aeronautics
ISSN: 1000-9361
Published: Elsevier BV 2024
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URI: https://cronfa.swan.ac.uk/Record/cronfa64692
first_indexed 2023-10-10T11:01:52Z
last_indexed 2024-11-25T14:14:32Z
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spelling 2024-04-11T13:08:09.6752180 v2 64692 2023-10-10 Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft cdadbd9e334ad914d7968a538d9522a4 Ye Yuan Ye Yuan true false 2023-10-10 ACEM Manned multi-rotor electric Vertical Takeoff and Landing (eVTOL) aircraft is prone to actuator saturation due to its weak yaw control efficiency. To address this inherent problem, a rotor cross-tilt configuration is applied in this paper, with an optimization method proposed to improve the overall control efficiency of the vehicle. First, a flight dynamics model of a 500-kg manned multi-rotor eVTOL aircraft is established. The accuracy of the co-axial rotor model is verified using a single arm test bench, and the accuracy of the flight dynamics model is verified by the flight test data. Then, an optimization method is designed based on the flight dynamics model to calculate an optimal rotor cross-tilt mounting angle, which not only improves the yaw control efficiency, but also basically maintains the efficiency of other control channels. The ideal rotor cross-tilt mounting angle for the prototype is determined by comprehensively considering the optimal results with different payloads, forward flight speeds, and rotor mounting angle errors. Finally, the feasibility of the rotor cross-tilt mounting angle is proved by analyzing the control derivatives of the flight dynamics model, the test data of a ground three Degree-of-Freedom (3DOF) platform, and the actual flight data of the prototype. The results show that a fixed rotor cross-tilt mounting angle can achieve ideal yaw control effectiveness, improving yaw angle tracking and hold ability, increasing endurance time, and achieving good yaw control performance with different payloads and forward speeds. Journal Article Chinese Journal of Aeronautics 37 3 153 167 Elsevier BV 1000-9361 Multi-rotor eVTOL, Control efficiency, Flight dynamics model, Cross-tilt optimization, Endurance time 1 3 2024 2024-03-01 10.1016/j.cja.2023.09.016 COLLEGE NANME Aerospace, Civil, Electrical, and Mechanical Engineering COLLEGE CODE ACEM Swansea University This study was co-supported by the National Natural Science Foundation of China (Nos. 12202406, 11672128). 2024-04-11T13:08:09.6752180 2023-10-10T11:59:40.9935590 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering Xufei YAN 0000-0002-6852-5845 1 Ye Yuan 2 Yanqin ZHAO 0000-0002-4179-6645 3 Renliang CHEN 4 64692__29994__e794c2bcd8214fada3af3d65864740f7.pdf 64692.VOR.pdf 2024-04-11T13:06:46.5937379 Output 4240742 application/pdf Version of Record true This is an open access article under the CC BY-NC-ND license. true eng http://creativecommons.org/licenses/by-nc-nd/4.0/
title Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft
spellingShingle Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft
Ye Yuan
title_short Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft
title_full Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft
title_fullStr Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft
title_full_unstemmed Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft
title_sort Rotor cross-tilt optimization for yaw control improvement of multi-rotor eVTOL aircraft
author_id_str_mv cdadbd9e334ad914d7968a538d9522a4
author_id_fullname_str_mv cdadbd9e334ad914d7968a538d9522a4_***_Ye Yuan
author Ye Yuan
author2 Xufei YAN
Ye Yuan
Yanqin ZHAO
Renliang CHEN
format Journal article
container_title Chinese Journal of Aeronautics
container_volume 37
container_issue 3
container_start_page 153
publishDate 2024
institution Swansea University
issn 1000-9361
doi_str_mv 10.1016/j.cja.2023.09.016
publisher Elsevier BV
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
document_store_str 1
active_str 0
description Manned multi-rotor electric Vertical Takeoff and Landing (eVTOL) aircraft is prone to actuator saturation due to its weak yaw control efficiency. To address this inherent problem, a rotor cross-tilt configuration is applied in this paper, with an optimization method proposed to improve the overall control efficiency of the vehicle. First, a flight dynamics model of a 500-kg manned multi-rotor eVTOL aircraft is established. The accuracy of the co-axial rotor model is verified using a single arm test bench, and the accuracy of the flight dynamics model is verified by the flight test data. Then, an optimization method is designed based on the flight dynamics model to calculate an optimal rotor cross-tilt mounting angle, which not only improves the yaw control efficiency, but also basically maintains the efficiency of other control channels. The ideal rotor cross-tilt mounting angle for the prototype is determined by comprehensively considering the optimal results with different payloads, forward flight speeds, and rotor mounting angle errors. Finally, the feasibility of the rotor cross-tilt mounting angle is proved by analyzing the control derivatives of the flight dynamics model, the test data of a ground three Degree-of-Freedom (3DOF) platform, and the actual flight data of the prototype. The results show that a fixed rotor cross-tilt mounting angle can achieve ideal yaw control effectiveness, improving yaw angle tracking and hold ability, increasing endurance time, and achieving good yaw control performance with different payloads and forward speeds.
published_date 2024-03-01T18:19:26Z
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score 11.059359

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