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Conceptual study of a morphing winglet based on unsymmetrical stiffness
Aerospace Science and Technology
Swansea University Authors:
Michael Friswell, Hamed Haddad Khodaparast
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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...
Published in: | Aerospace Science and Technology |
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ISSN: | 1270-9638 |
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2016
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URI: | https://cronfa.swan.ac.uk/Record/cronfa30222 |
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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 |
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facultyofscienceandengineering |
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Faculty of Science and Engineering |
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facultyofscienceandengineering |
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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 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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1763751610680344576 |
score |
11.021648 |