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Conceptual study of a morphing winglet based on unsymmetrical stiffness

Chen Wang, Hamed Haddad Khodaparast, Michael Friswell, Hamed Haddad Khodaparast Orcid Logo

Aerospace Science and Technology

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

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DOI (Published version): 10.1016/j.ast.2016.09.015

Abstract

Morphing technology has the potential to increase aircraft performance. Among the morphing technologies, the morphing winglet is a promising solution due to its small size and large effect on the aerodynamics. Morphing winglets have to carry the spanwise aerodynamic loads, with low weight and small...

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Published in: Aerospace Science and Technology
ISSN: 1270-9638
Published: 2016
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URI: https://cronfa.swan.ac.uk/Record/cronfa30222
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first_indexed 2016-09-27T03:55:32Z
last_indexed 2018-02-09T05:15:58Z
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spelling 2016-10-05T16:07:22.3768750 v2 30222 2016-09-26 Conceptual study of a morphing winglet based on unsymmetrical stiffness 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false f207b17edda9c4c3ea074cbb7555efc1 0000-0002-3721-4980 Hamed Haddad Khodaparast Hamed Haddad Khodaparast true false 2016-09-26 FGSEN Morphing technology has the potential to increase aircraft performance. Among the morphing technologies, the morphing winglet is a promising solution due to its small size and large effect on the aerodynamics. Morphing winglets have to carry the spanwise aerodynamic loads, with low weight and small size. This makes the design of a reliable morphing structure of great importance to realize a morphing winglet.In this paper, a novel compliant structure is proposed based on the concept of unsymmetrical stiffness. The morphing winglet has to change its dihedral angle, and its stiffness has to be large enough to carry loads. While increasing the total stiffness, the allocation of the stiffness can be unsymmetrical, introducing deformation under a linear actuation force. If the total stiffness and its asymmetry are properly designed, the final deformation under both aerodynamic loads and actuation force can be optimized. The current study uses different composite layups of round corrugation structures to provide the stiffness asymmetry. A simplified model is developed to estimate the induced deformation and required actuation force. The deformation limit of the structure is also predicted using detailed finite element analysis.To demonstrate the application of the morphing structure, the baseline design of a regional twin turboprop airliner is generated. A worm and rack actuation mechanism is also designed. For performance analysis, the weight due to the morphing winglet and its actuation system is estimated. The influence of retrofitting the baseline design is investigated to obtain a trade-off design for the morphing structure.From the conceptual study, the simplified approach provides the basic properties of the morphing structure to retrofit the baseline aircraft, which highlights the feasibility of this novel concept although further study is still needed for its detailed design and analysis. Journal Article Aerospace Science and Technology 1270-9638 31 12 2016 2016-12-31 10.1016/j.ast.2016.09.015 COLLEGE NANME Science and Engineering - Faculty COLLEGE CODE FGSEN Swansea University 2016-10-05T16:07:22.3768750 2016-09-26T21:32:42.3436926 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised Chen Wang 1 Hamed Haddad Khodaparast 2 Michael Friswell 3 Hamed Haddad Khodaparast 0000-0002-3721-4980 4 0030222-05102016160637.pdf wang2016(2).pdf 2016-10-05T16:06:37.2770000 Output 1553216 application/pdf Accepted Manuscript true 2017-09-22T00:00:00.0000000 false
title Conceptual study of a morphing winglet based on unsymmetrical stiffness
spellingShingle Conceptual study of a morphing winglet based on unsymmetrical stiffness
Michael Friswell
Hamed Haddad Khodaparast
title_short Conceptual study of a morphing winglet based on unsymmetrical stiffness
title_full Conceptual study of a morphing winglet based on unsymmetrical stiffness
title_fullStr Conceptual study of a morphing winglet based on unsymmetrical stiffness
title_full_unstemmed Conceptual study of a morphing winglet based on unsymmetrical stiffness
title_sort Conceptual study of a morphing winglet based on unsymmetrical stiffness
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 Chen Wang
Hamed Haddad Khodaparast
Michael Friswell
Hamed Haddad Khodaparast
format Journal article
container_title Aerospace Science and Technology
publishDate 2016
institution Swansea University
issn 1270-9638
doi_str_mv 10.1016/j.ast.2016.09.015
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 Morphing technology has the potential to increase aircraft performance. Among the morphing technologies, the morphing winglet is a promising solution due to its small size and large effect on the aerodynamics. Morphing winglets have to carry the spanwise aerodynamic loads, with low weight and small size. This makes the design of a reliable morphing structure of great importance to realize a morphing winglet.In this paper, a novel compliant structure is proposed based on the concept of unsymmetrical stiffness. The morphing winglet has to change its dihedral angle, and its stiffness has to be large enough to carry loads. While increasing the total stiffness, the allocation of the stiffness can be unsymmetrical, introducing deformation under a linear actuation force. If the total stiffness and its asymmetry are properly designed, the final deformation under both aerodynamic loads and actuation force can be optimized. The current study uses different composite layups of round corrugation structures to provide the stiffness asymmetry. A simplified model is developed to estimate the induced deformation and required actuation force. The deformation limit of the structure is also predicted using detailed finite element analysis.To demonstrate the application of the morphing structure, the baseline design of a regional twin turboprop airliner is generated. A worm and rack actuation mechanism is also designed. For performance analysis, the weight due to the morphing winglet and its actuation system is estimated. The influence of retrofitting the baseline design is investigated to obtain a trade-off design for the morphing structure.From the conceptual study, the simplified approach provides the basic properties of the morphing structure to retrofit the baseline aircraft, which highlights the feasibility of this novel concept although further study is still needed for its detailed design and analysis.
published_date 2016-12-31T03:36:51Z
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score 11.01753

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