Journal article 819 views 142 downloads
Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
,
Abbas Mazidi,
Jonathan E. Cooper
Aerospace, Volume: 8, Issue: 4, Start page: 100
Swansea University Authors:
Michael Friswell, Hamed Haddad Khodaparast
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DOI (Published version): 10.3390/aerospace8040100
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...
| Published in: | Aerospace |
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| ISSN: | 2226-4310 |
| Published: |
MDPI AG
2021
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| Online Access: |
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| URI: | https://cronfa.swan.ac.uk/Record/cronfa56724 |
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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 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. |
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| Keywords: |
aeroelastic stability; intrinsic formulation; electric aircraft; distributed electric propulsion; unsteady aerodynamics |
| College: |
Faculty of Science and Engineering |
| Issue: |
4 |
| Start Page: |
100 |