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Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors

Mohammadreza Amoozgar, Michael Friswell, Seyed Ahmad Fazelzadeh, Hamed Haddad Khodaparast Orcid Logo, Abbas Mazidi, Jonathan E. Cooper

Aerospace, Volume: 8, Issue: 4, Start page: 100

Swansea University Authors: Michael Friswell, Hamed Haddad Khodaparast Orcid Logo

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Abstract

In this paper, the effect of distributed electric propulsion on the aeroelastic stability of an electric aircraft wing was investigated. All the electric propulsors, which are of different properties, are attached to the wing of the aircraft in different positions. The wing structural dynamics was m...

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Published in: Aerospace
ISSN: 2226-4310
Published: MDPI AG 2021
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URI: https://cronfa.swan.ac.uk/Record/cronfa56724
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spelling 2021-05-18T12:56:36.4357946 v2 56724 2021-04-23 Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false f207b17edda9c4c3ea074cbb7555efc1 0000-0002-3721-4980 Hamed Haddad Khodaparast Hamed Haddad Khodaparast true false 2021-04-23 FGSEN In this paper, the effect of distributed electric propulsion on the aeroelastic stability of an electric aircraft wing was investigated. All the electric propulsors, which are of different properties, are attached to the wing of the aircraft in different positions. The wing structural dynamics was modelled by using geometrically exact beam equations, while the aerodynamic loads were simulated by using an unsteady aerodynamic theory. The electric propulsors were modelled by using a concentrated mass attached to the wing, and the motor’s thrust and angular momentum were taken into account. The thrust of each propulsor was modelled as a follower force acting exactly at the centre of gravity of the propulsor. The nonlinear aeroelastic governing equations were discretised using a time–space scheme, and the obtained results were verified against available results and very good agreement was observed. Two case studies were considered throughout the paper, resembling two flight conditions of the electric aircraft. The numerical results show that the tip propulsor thrust, mass, and angular momentum had the most impact on the aeroelastic stability of the wing. In addition, it was observed that the high-lift motors had a minimal effect on the aeroelastic stability of the wing. Journal Article Aerospace 8 4 100 MDPI AG 2226-4310 aeroelastic stability; intrinsic formulation; electric aircraft; distributed electric propulsion; unsteady aerodynamics 2 4 2021 2021-04-02 10.3390/aerospace8040100 COLLEGE NANME Science and Engineering - Faculty COLLEGE CODE FGSEN Swansea University 2021-05-18T12:56:36.4357946 2021-04-23T09:13:25.2202456 College of Engineering Engineering Mohammadreza Amoozgar 1 Michael Friswell 2 Seyed Ahmad Fazelzadeh 3 Hamed Haddad Khodaparast 0000-0002-3721-4980 4 Abbas Mazidi 5 Jonathan E. Cooper 6 56724__19741__20f553d37f8a42bd886838dd2d28dce6.pdf 56724.pdf 2021-04-23T09:15:30.8817412 Output 1223005 application/pdf Version of Record true © 2021 by the authors. This is an open access article distributed under the terms of the Creative Commons Attribution (CC BY) license true eng http://creativecommons.org/licenses/by/4.0/
title Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
spellingShingle Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
Michael Friswell
Hamed Haddad Khodaparast
title_short Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
title_full Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
title_fullStr Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
title_full_unstemmed Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
title_sort Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
author_id_str_mv 5894777b8f9c6e64bde3568d68078d40
f207b17edda9c4c3ea074cbb7555efc1
author_id_fullname_str_mv 5894777b8f9c6e64bde3568d68078d40_***_Michael Friswell
f207b17edda9c4c3ea074cbb7555efc1_***_Hamed Haddad Khodaparast
author Michael Friswell
Hamed Haddad Khodaparast
author2 Mohammadreza Amoozgar
Michael Friswell
Seyed Ahmad Fazelzadeh
Hamed Haddad Khodaparast
Abbas Mazidi
Jonathan E. Cooper
format Journal article
container_title Aerospace
container_volume 8
container_issue 4
container_start_page 100
publishDate 2021
institution Swansea University
issn 2226-4310
doi_str_mv 10.3390/aerospace8040100
publisher MDPI AG
college_str College of Engineering
hierarchytype
hierarchy_top_id collegeofengineering
hierarchy_top_title College of Engineering
hierarchy_parent_id collegeofengineering
hierarchy_parent_title College of Engineering
department_str Engineering{{{_:::_}}}College of Engineering{{{_:::_}}}Engineering
document_store_str 1
active_str 0
description In this paper, the effect of distributed electric propulsion on the aeroelastic stability of an electric aircraft wing was investigated. All the electric propulsors, which are of different properties, are attached to the wing of the aircraft in different positions. The wing structural dynamics was modelled by using geometrically exact beam equations, while the aerodynamic loads were simulated by using an unsteady aerodynamic theory. The electric propulsors were modelled by using a concentrated mass attached to the wing, and the motor’s thrust and angular momentum were taken into account. The thrust of each propulsor was modelled as a follower force acting exactly at the centre of gravity of the propulsor. The nonlinear aeroelastic governing equations were discretised using a time–space scheme, and the obtained results were verified against available results and very good agreement was observed. Two case studies were considered throughout the paper, resembling two flight conditions of the electric aircraft. The numerical results show that the tip propulsor thrust, mass, and angular momentum had the most impact on the aeroelastic stability of the wing. In addition, it was observed that the high-lift motors had a minimal effect on the aeroelastic stability of the wing.
published_date 2021-04-02T04:12:27Z
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score 10.8781185