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Optimisation of composite corrugated skins for buckling in morphing aircraft

I. Dayyani, M.I. Friswell, Michael Friswell, Alexander Shaw Orcid Logo

Composite Structures, Volume: 119, Pages: 227 - 237

Swansea University Authors: Michael Friswell, Alexander Shaw Orcid Logo

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DOI (Published version): 10.1016/j.compstruct.2014.09.001

Abstract

Morphing Aircraft aim to increase the performance of aircraft over multiple flight conditions, by enabling shape changes in flight in order to optimise their aerodynamic properties for the current conditions. The skin of a morphing aircraft is a critical component.It must be compliant in degrees of...

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Published in: Composite Structures
ISSN: 0263-8223
Published: 2015
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URI: https://cronfa.swan.ac.uk/Record/cronfa18747
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first_indexed 2015-05-15T01:57:42Z
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spelling 2022-11-15T16:20:25.4559424 v2 18747 2014-10-17 Optimisation of composite corrugated skins for buckling in morphing aircraft 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 10cb5f545bc146fba9a542a1d85f2dea 0000-0002-7521-827X Alexander Shaw Alexander Shaw true false 2014-10-17 FGSEN Morphing Aircraft aim to increase the performance of aircraft over multiple flight conditions, by enabling shape changes in flight in order to optimise their aerodynamic properties for the current conditions. The skin of a morphing aircraft is a critical component.It must be compliant in degrees of freedom that are required for actuation, to minimise the actuation loads. However, it must also carry structural loads, and therefore be stiff in load bearing degrees of freedom. This leads to a requirement for extremely anisotropic material systems. A common solution is the use of a corrugated panel. However, previous work on corrugations has not addressed the problem of compressive buckling loads. This work analyses the performance of corrugated panels under buckling loads, and optimises corrugation patterns for the objectives of weight, buckling performance, and actuation compliance. Simplified analytical models that derive properties equivalent to conventional plates are used to obtain approximate estimates of the buckling loads. Furthermore a new mode of buckling, that occurs entirely in-plane and is unique to panels with extreme anisotropy is analysed. The simple models allow optimisation to be performed, and both a single-objective and a multi-objective approach are demonstrated. The results are compared to Finite Element Analysis. Journal Article Composite Structures 119 227 237 0263-8223 31 1 2015 2015-01-31 10.1016/j.compstruct.2014.09.001 COLLEGE NANME Science and Engineering - Faculty COLLEGE CODE FGSEN Swansea University 2022-11-15T16:20:25.4559424 2014-10-17T11:37:54.4437653 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised I. Dayyani 1 M.I. Friswell 2 Michael Friswell 3 Alexander Shaw 0000-0002-7521-827X 4
title Optimisation of composite corrugated skins for buckling in morphing aircraft
spellingShingle Optimisation of composite corrugated skins for buckling in morphing aircraft
Michael Friswell
Alexander Shaw
title_short Optimisation of composite corrugated skins for buckling in morphing aircraft
title_full Optimisation of composite corrugated skins for buckling in morphing aircraft
title_fullStr Optimisation of composite corrugated skins for buckling in morphing aircraft
title_full_unstemmed Optimisation of composite corrugated skins for buckling in morphing aircraft
title_sort Optimisation of composite corrugated skins for buckling in morphing aircraft
author_id_str_mv 5894777b8f9c6e64bde3568d68078d40
10cb5f545bc146fba9a542a1d85f2dea
author_id_fullname_str_mv 5894777b8f9c6e64bde3568d68078d40_***_Michael Friswell
10cb5f545bc146fba9a542a1d85f2dea_***_Alexander Shaw
author Michael Friswell
Alexander Shaw
author2 I. Dayyani
M.I. Friswell
Michael Friswell
Alexander Shaw
format Journal article
container_title Composite Structures
container_volume 119
container_start_page 227
publishDate 2015
institution Swansea University
issn 0263-8223
doi_str_mv 10.1016/j.compstruct.2014.09.001
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 0
active_str 0
description Morphing Aircraft aim to increase the performance of aircraft over multiple flight conditions, by enabling shape changes in flight in order to optimise their aerodynamic properties for the current conditions. The skin of a morphing aircraft is a critical component.It must be compliant in degrees of freedom that are required for actuation, to minimise the actuation loads. However, it must also carry structural loads, and therefore be stiff in load bearing degrees of freedom. This leads to a requirement for extremely anisotropic material systems. A common solution is the use of a corrugated panel. However, previous work on corrugations has not addressed the problem of compressive buckling loads. This work analyses the performance of corrugated panels under buckling loads, and optimises corrugation patterns for the objectives of weight, buckling performance, and actuation compliance. Simplified analytical models that derive properties equivalent to conventional plates are used to obtain approximate estimates of the buckling loads. Furthermore a new mode of buckling, that occurs entirely in-plane and is unique to panels with extreme anisotropy is analysed. The simple models allow optimisation to be performed, and both a single-objective and a multi-objective approach are demonstrated. The results are compared to Finite Element Analysis.
published_date 2015-01-31T03:22:01Z
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score 11.019224

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