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Aeroelastic model and analysis of an active camber morphing wing

Jiaying Zhang Orcid Logo, Alexander Shaw Orcid Logo, Chen Wang, Huaiyuan Gu, Mohammadreza Amoozgar, Michael Friswell, Benjamin K.S. Woods

Aerospace Science and Technology, Volume: 111, Start page: 106534

Swansea University Authors: Jiaying Zhang Orcid Logo, Alexander Shaw Orcid Logo, Michael Friswell

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DOI (Published version): 10.1016/j.ast.2021.106534

Abstract

Morphing aircraft structures usually introduce greater compliance into aerodynamic sections, and therefore will affect the aeroelasticity with the potential risk of increased flutter. A low-fidelity model of an active camber morphing wing and its aeroelastic model are developed in order to investiga...

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Published in: Aerospace Science and Technology
ISSN: 1270-9638
Published: Elsevier BV 2021
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URI: https://cronfa.swan.ac.uk/Record/cronfa56219
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A low-fidelity model of an active camber morphing wing and its aeroelastic model are developed in order to investigate the potential critical speed by exploiting its chord-wise dimension and flexibility. Such a model may be used for conceptual design, where low fidelity models are used to explore and optimise a wide range of configurations. The morphing camber concept is implemented using a continuous representation of a two-segment structure with a rigid segment and a deformable part. The aeroelastic model is developed based on both steady and unsteady aerodynamic models, so that different parameters can be easily modified to examine changes in the flutter solutions. Of particular interest are the ratio of the morphing segment length to the chord, and its relative stiffness, as such morphing camber is potential operated using the deformable part as a flap. By comparing the results of the quasi-steady and unsteady aerodynamic models, it is shown that the quasi-steady aerodynamic model gives a more conservative prediction of the flutter speed. In addition, responses in phase space are simulated to show the fundamental aeroelastic behaviour of the morphing camber wing. It is also shown that the active compliant segment can be used to stabilise the morphing aircraft by using feedback control. 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spelling 2021-03-03T11:38:09.0013957 v2 56219 2021-02-09 Aeroelastic model and analysis of an active camber morphing wing 12b61893c794b14f11cf0a84cb947d0e 0000-0001-7308-5090 Jiaying Zhang Jiaying Zhang true false 10cb5f545bc146fba9a542a1d85f2dea 0000-0002-7521-827X Alexander Shaw Alexander Shaw true false 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 2021-02-09 EEN Morphing aircraft structures usually introduce greater compliance into aerodynamic sections, and therefore will affect the aeroelasticity with the potential risk of increased flutter. A low-fidelity model of an active camber morphing wing and its aeroelastic model are developed in order to investigate the potential critical speed by exploiting its chord-wise dimension and flexibility. Such a model may be used for conceptual design, where low fidelity models are used to explore and optimise a wide range of configurations. The morphing camber concept is implemented using a continuous representation of a two-segment structure with a rigid segment and a deformable part. The aeroelastic model is developed based on both steady and unsteady aerodynamic models, so that different parameters can be easily modified to examine changes in the flutter solutions. Of particular interest are the ratio of the morphing segment length to the chord, and its relative stiffness, as such morphing camber is potential operated using the deformable part as a flap. By comparing the results of the quasi-steady and unsteady aerodynamic models, it is shown that the quasi-steady aerodynamic model gives a more conservative prediction of the flutter speed. In addition, responses in phase space are simulated to show the fundamental aeroelastic behaviour of the morphing camber wing. It is also shown that the active compliant segment can be used to stabilise the morphing aircraft by using feedback control. This paper provides a system-level insight through mathematical modelling, parameter analysis and feedback control into dynamics applications of morphing camber. Journal Article Aerospace Science and Technology 111 106534 Elsevier BV 1270-9638 Morphing camber, Rigid-flexible structure, Flutter, Feedback control 1 4 2021 2021-04-01 10.1016/j.ast.2021.106534 COLLEGE NANME Engineering COLLEGE CODE EEN Swansea University 2021-03-03T11:38:09.0013957 2021-02-09T10:56:58.5916382 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised Jiaying Zhang 0000-0001-7308-5090 1 Alexander Shaw 0000-0002-7521-827X 2 Chen Wang 3 Huaiyuan Gu 4 Mohammadreza Amoozgar 5 Michael Friswell 6 Benjamin K.S. Woods 7 56219__19265__7491912238394a5790550f52a7c82e28.pdf 56219.pdf 2021-02-11T11:29:43.0725509 Output 3484297 application/pdf Accepted Manuscript true 2022-01-28T00:00:00.0000000 ©2021 All rights reserved. All article content, except where otherwise noted, is licensed under a Creative Commons Attribution Non-Commercial No Derivatives License (CC-BY-NC-ND) true eng http://creativecommons.org/licenses/by-nc-nd/4.0/
title Aeroelastic model and analysis of an active camber morphing wing
spellingShingle Aeroelastic model and analysis of an active camber morphing wing
Jiaying Zhang
Alexander Shaw
Michael Friswell
title_short Aeroelastic model and analysis of an active camber morphing wing
title_full Aeroelastic model and analysis of an active camber morphing wing
title_fullStr Aeroelastic model and analysis of an active camber morphing wing
title_full_unstemmed Aeroelastic model and analysis of an active camber morphing wing
title_sort Aeroelastic model and analysis of an active camber morphing wing
author_id_str_mv 12b61893c794b14f11cf0a84cb947d0e
10cb5f545bc146fba9a542a1d85f2dea
5894777b8f9c6e64bde3568d68078d40
author_id_fullname_str_mv 12b61893c794b14f11cf0a84cb947d0e_***_Jiaying Zhang
10cb5f545bc146fba9a542a1d85f2dea_***_Alexander Shaw
5894777b8f9c6e64bde3568d68078d40_***_Michael Friswell
author Jiaying Zhang
Alexander Shaw
Michael Friswell
author2 Jiaying Zhang
Alexander Shaw
Chen Wang
Huaiyuan Gu
Mohammadreza Amoozgar
Michael Friswell
Benjamin K.S. Woods
format Journal article
container_title Aerospace Science and Technology
container_volume 111
container_start_page 106534
publishDate 2021
institution Swansea University
issn 1270-9638
doi_str_mv 10.1016/j.ast.2021.106534
publisher Elsevier BV
college_str Faculty of Science and Engineering
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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 Engineering and Applied Sciences - Uncategorised{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Engineering and Applied Sciences - Uncategorised
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description Morphing aircraft structures usually introduce greater compliance into aerodynamic sections, and therefore will affect the aeroelasticity with the potential risk of increased flutter. A low-fidelity model of an active camber morphing wing and its aeroelastic model are developed in order to investigate the potential critical speed by exploiting its chord-wise dimension and flexibility. Such a model may be used for conceptual design, where low fidelity models are used to explore and optimise a wide range of configurations. The morphing camber concept is implemented using a continuous representation of a two-segment structure with a rigid segment and a deformable part. The aeroelastic model is developed based on both steady and unsteady aerodynamic models, so that different parameters can be easily modified to examine changes in the flutter solutions. Of particular interest are the ratio of the morphing segment length to the chord, and its relative stiffness, as such morphing camber is potential operated using the deformable part as a flap. By comparing the results of the quasi-steady and unsteady aerodynamic models, it is shown that the quasi-steady aerodynamic model gives a more conservative prediction of the flutter speed. In addition, responses in phase space are simulated to show the fundamental aeroelastic behaviour of the morphing camber wing. It is also shown that the active compliant segment can be used to stabilise the morphing aircraft by using feedback control. This paper provides a system-level insight through mathematical modelling, parameter analysis and feedback control into dynamics applications of morphing camber.
published_date 2021-04-01T04:11:01Z
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