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Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft

Ye Yuan Orcid Logo, Douglas Thomson, David Anderson

Aerospace, Volume: 9, Issue: 5, Start page: 271

Swansea University Author: Ye Yuan Orcid Logo

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DOI (Published version): 10.3390/aerospace9050271

Abstract

The tiltrotor has unique flight dynamics due to the aerodynamic interference characteristics. Multiple aerodynamics calculation approaches, such as the CFD method, are utilised to characterise this feature. The calculation process is usually time-consuming, and the obtained results are generally var...

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Published in: Aerospace
ISSN: 2226-4310
Published: MDPI AG 2022
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URI: https://cronfa.swan.ac.uk/Record/cronfa60064
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first_indexed 2022-05-23T21:14:02Z
last_indexed 2022-06-24T03:19:04Z
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spelling 2022-06-23T13:20:36.4749222 v2 60064 2022-05-23 Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft cdadbd9e334ad914d7968a538d9522a4 0000-0002-7568-0130 Ye Yuan Ye Yuan true false 2022-05-23 GENG The tiltrotor has unique flight dynamics due to the aerodynamic interference characteristics. Multiple aerodynamics calculation approaches, such as the CFD method, are utilised to characterise this feature. The calculation process is usually time-consuming, and the obtained results are generally varied from each other. Thus, the uncertainty quantification (UQ) method will be utilised in this research to identify the aerodynamic inaccuracy effect on the handling qualities of the tiltrotor aircraft. The study aims to quantify the influence of the aerodynamic interference on the tiltrotor flight dynamics in different flight states, such as forward speeds and nacelle tilting angles, which can guide the flight dynamics modelling simplification to improve the simulation efficiency. Therefore, uncertainty identification and full factorial numerical integration (FFNI) methods are introduced to scale these aerodynamic uncertainties. The eigenvalue and bandwidth and phase delay requirements are presented as the failure criteria. The UQ calculation indicates that the uncertainties of the aerodynamic calculation significantly affect the handling quality ratings in two flight ranges: the helicopter mode and the conversion and aeroplane modes with higher forward speed (close to the conversion envelope). Furthermore, a sensitivity analysis is performed to identify the mechanism behind these influences. The results demonstrate that aerodynamics affect the pitching attitude, the pitching damping, and the velocity and incidence stability derivatives. However, the effects of the velocity stability and the incidence stability are the reason causing the handling qualities’ degradation in the helicopter mode and high-speed mode, respectively. Journal Article Aerospace 9 5 271 MDPI AG 2226-4310 tiltrotor; uncertainty quantification; handling qualities; flight dynamics 18 5 2022 2022-05-18 10.3390/aerospace9050271 COLLEGE NANME General Engineering COLLEGE CODE GENG Swansea University Not Required The financial support of the EPSRC project MENtOR: Methods and Experiments for NOvel Rotorcraft EP/S013814/1, is gratefully acknowledged. 2022-06-23T13:20:36.4749222 2022-05-23T22:10:14.0546352 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering Ye Yuan 0000-0002-7568-0130 1 Douglas Thomson 2 David Anderson 3 60064__24380__913cdc54bcbf41c1aad36c5eebaec938.pdf 60064.pdf 2022-06-23T13:17:30.3212120 Output 3048027 application/pdf Version of Record true © 2022 by the authors. This is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license true eng https://creativecommons.org/licenses/by/4.0/
title Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft
spellingShingle Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft
Ye Yuan
title_short Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft
title_full Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft
title_fullStr Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft
title_full_unstemmed Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft
title_sort Aerodynamic Uncertainty Quantification for Tiltrotor Aircraft
author_id_str_mv cdadbd9e334ad914d7968a538d9522a4
author_id_fullname_str_mv cdadbd9e334ad914d7968a538d9522a4_***_Ye Yuan
author Ye Yuan
author2 Ye Yuan
Douglas Thomson
David Anderson
format Journal article
container_title Aerospace
container_volume 9
container_issue 5
container_start_page 271
publishDate 2022
institution Swansea University
issn 2226-4310
doi_str_mv 10.3390/aerospace9050271
publisher MDPI AG
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 - General Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering
document_store_str 1
active_str 0
description The tiltrotor has unique flight dynamics due to the aerodynamic interference characteristics. Multiple aerodynamics calculation approaches, such as the CFD method, are utilised to characterise this feature. The calculation process is usually time-consuming, and the obtained results are generally varied from each other. Thus, the uncertainty quantification (UQ) method will be utilised in this research to identify the aerodynamic inaccuracy effect on the handling qualities of the tiltrotor aircraft. The study aims to quantify the influence of the aerodynamic interference on the tiltrotor flight dynamics in different flight states, such as forward speeds and nacelle tilting angles, which can guide the flight dynamics modelling simplification to improve the simulation efficiency. Therefore, uncertainty identification and full factorial numerical integration (FFNI) methods are introduced to scale these aerodynamic uncertainties. The eigenvalue and bandwidth and phase delay requirements are presented as the failure criteria. The UQ calculation indicates that the uncertainties of the aerodynamic calculation significantly affect the handling quality ratings in two flight ranges: the helicopter mode and the conversion and aeroplane modes with higher forward speed (close to the conversion envelope). Furthermore, a sensitivity analysis is performed to identify the mechanism behind these influences. The results demonstrate that aerodynamics affect the pitching attitude, the pitching damping, and the velocity and incidence stability derivatives. However, the effects of the velocity stability and the incidence stability are the reason causing the handling qualities’ degradation in the helicopter mode and high-speed mode, respectively.
published_date 2022-05-18T04:17:51Z
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score 11.037603

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