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Predicting Global Strain Limits for Corrugated Panels

C. Wang, Yuying Xia, Michael Friswell, E.I. Saavedra Flores

Composite Structures, Start page: 111472

Swansea University Authors: Yuying Xia, Michael Friswell

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DOI (Published version): 10.1016/j.compstruct.2019.111472

Abstract

Corrugated panels have many potential applications in civil, mechanical and aerospace engineering. The research on morphing aircraft requires the derivation of deformation limits of corrugated panels, which can be used as the constraint conditions for the design and optimisation of morphing structur...

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Published in: Composite Structures
ISSN: 0263-8223
Published: 2019
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URI: https://cronfa.swan.ac.uk/Record/cronfa52108
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first_indexed 2019-09-26T14:20:13Z
last_indexed 2020-11-21T04:06:17Z
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spelling 2020-11-20T12:42:00.1272741 v2 52108 2019-09-26 Predicting Global Strain Limits for Corrugated Panels 483e362fc8a1510c358421ef303aff69 Yuying Xia Yuying Xia true false 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 2019-09-26 AERO Corrugated panels have many potential applications in civil, mechanical and aerospace engineering. The research on morphing aircraft requires the derivation of deformation limits of corrugated panels, which can be used as the constraint conditions for the design and optimisation of morphing structures. The relationship between the local and global strains of the equivalent models for corrugated panels is derived, which makes the prediction of the maximum strain available. Thus, from the maximum strain criterion, the global strain limit is evaluated under different load conditions. The results from the proposed analytical method are compared to those from detailed finite element models, which indicates a good agreement for all of the analysed cases. The influence of the geometric parameters of the corrugation shape is also investigated. Journal Article Composite Structures 111472 0263-8223 Corrugated panel, equivalent orthotropic plate, equivalent model, strain limit, morphing skin 31 12 2019 2019-12-31 10.1016/j.compstruct.2019.111472 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University 2020-11-20T12:42:00.1272741 2019-09-26T10:07:29.0326029 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised C. Wang 1 Yuying Xia 2 Michael Friswell 3 E.I. Saavedra Flores 4 0052108-26092019101038.pdf wang2019(4).pdf 2019-09-26T10:10:38.7800000 Output 848092 application/pdf Accepted Manuscript true 2020-09-17T00:00:00.0000000 © 2019. This manuscript version is made available under the CC-BY-NC-ND 4.0 license http://creativecommons.org/licenses/by-nc-nd/4.0/ false eng
title Predicting Global Strain Limits for Corrugated Panels
spellingShingle Predicting Global Strain Limits for Corrugated Panels
Yuying Xia
Michael Friswell
title_short Predicting Global Strain Limits for Corrugated Panels
title_full Predicting Global Strain Limits for Corrugated Panels
title_fullStr Predicting Global Strain Limits for Corrugated Panels
title_full_unstemmed Predicting Global Strain Limits for Corrugated Panels
title_sort Predicting Global Strain Limits for Corrugated Panels
author_id_str_mv 483e362fc8a1510c358421ef303aff69
5894777b8f9c6e64bde3568d68078d40
author_id_fullname_str_mv 483e362fc8a1510c358421ef303aff69_***_Yuying Xia
5894777b8f9c6e64bde3568d68078d40_***_Michael Friswell
author Yuying Xia
Michael Friswell
author2 C. Wang
Yuying Xia
Michael Friswell
E.I. Saavedra Flores
format Journal article
container_title Composite Structures
container_start_page 111472
publishDate 2019
institution Swansea University
issn 0263-8223
doi_str_mv 10.1016/j.compstruct.2019.111472
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 Engineering and Applied Sciences - Uncategorised{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Engineering and Applied Sciences - Uncategorised
document_store_str 1
active_str 0
description Corrugated panels have many potential applications in civil, mechanical and aerospace engineering. The research on morphing aircraft requires the derivation of deformation limits of corrugated panels, which can be used as the constraint conditions for the design and optimisation of morphing structures. The relationship between the local and global strains of the equivalent models for corrugated panels is derived, which makes the prediction of the maximum strain available. Thus, from the maximum strain criterion, the global strain limit is evaluated under different load conditions. The results from the proposed analytical method are compared to those from detailed finite element models, which indicates a good agreement for all of the analysed cases. The influence of the geometric parameters of the corrugation shape is also investigated.
published_date 2019-12-31T04:04:18Z
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score 11.01753

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