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Compliant structures based on stiffness asymmetry

C. Wang, H. H. Khodaparast, M. I. Friswell, A. D. Shaw, Michael Friswell, Hamed Haddad Khodaparast Orcid Logo, Alexander Shaw Orcid Logo

The Aeronautical Journal, Volume: 122, Issue: 1249, Pages: 442 - 461

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

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DOI (Published version): 10.1017/aer.2017.144

Abstract

One of the key problems in the development of morphing aircraft is the morphing structure, which should be able to carry loads and change its geometry simultaneously. This paper investigates a compliant structure, which has the potential to change the dihedral angle of morphing wing-tip devices. The...

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Published in: The Aeronautical Journal
ISSN: 0001-9240 2059-6464
Published: Cambridge University Press 2018
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This paper investigates a compliant structure, which has the potential to change the dihedral angle of morphing wing-tip devices. The compliant structure is able to induce deformation by unsymmetrical stiffness allocation and carry aerodynamic loads if the total stiffness of the structure is sufficient.The concept has been introduced by building a simplified model of the structure and deriving the analytical equations. However, a properly designed stiffness asymmetry, which is optimised, can help to achieve the same deformation with a reduced actuation force.In this paper, round corrugated panels are used in the compliant structure and the stiffness asymmetry is introduced by changing the geometry of the corrugation panel. A new equivalent model of the round corrugated panel is developed, which takes the axial and bending coupling of the corrugated panel into account. The stiffness matrix of the corrugated panel is obtained using the equivalent model, and then the deflections of the compliant structure can be calculated. The results are compared to those from detailed finite element models built in the commercial software Abaqus. Samples with different geometries were manufactured for experimental tests.After verifying the equivalent model, optimisation is performed to find the optimum geometries of the compliant structures. The actuation force of a single compliant structure is first optimised, and then the optimisation is performed for a compliant structure consisting of multiple units. A case study is used to show the performance improvement obtained.</abstract><type>Journal Article</type><journal>The Aeronautical Journal</journal><volume>122</volume><journalNumber>1249</journalNumber><paginationStart>442</paginationStart><paginationEnd>461</paginationEnd><publisher>Cambridge University Press</publisher><placeOfPublication/><isbnPrint/><isbnElectronic/><issnPrint>0001-9240</issnPrint><issnElectronic>2059-6464</issnElectronic><keywords>Morphing aircraft; compliant structure; corrugated panel; optimisation</keywords><publishedDay>31</publishedDay><publishedMonth>3</publishedMonth><publishedYear>2018</publishedYear><publishedDate>2018-03-31</publishedDate><doi>10.1017/aer.2017.144</doi><url/><notes/><college>COLLEGE NANME</college><department>Science and Engineering - Faculty</department><CollegeCode>COLLEGE CODE</CollegeCode><DepartmentCode>FGSEN</DepartmentCode><institution>Swansea University</institution><apcterm/><lastEdited>2021-02-23T13:58:15.5325505</lastEdited><Created>2018-02-19T12:15:05.4428890</Created><path><level id="1">Faculty of Science and Engineering</level><level id="2">School of Engineering and Applied Sciences - Uncategorised</level></path><authors><author><firstname>C.</firstname><surname>Wang</surname><order>1</order></author><author><firstname>H. H.</firstname><surname>Khodaparast</surname><order>2</order></author><author><firstname>M. I.</firstname><surname>Friswell</surname><order>3</order></author><author><firstname>A. 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spelling 2021-02-23T13:58:15.5325505 v2 38777 2018-02-19 Compliant structures based on stiffness asymmetry 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false f207b17edda9c4c3ea074cbb7555efc1 0000-0002-3721-4980 Hamed Haddad Khodaparast Hamed Haddad Khodaparast true false 10cb5f545bc146fba9a542a1d85f2dea 0000-0002-7521-827X Alexander Shaw Alexander Shaw true false 2018-02-19 FGSEN One of the key problems in the development of morphing aircraft is the morphing structure, which should be able to carry loads and change its geometry simultaneously. This paper investigates a compliant structure, which has the potential to change the dihedral angle of morphing wing-tip devices. The compliant structure is able to induce deformation by unsymmetrical stiffness allocation and carry aerodynamic loads if the total stiffness of the structure is sufficient.The concept has been introduced by building a simplified model of the structure and deriving the analytical equations. However, a properly designed stiffness asymmetry, which is optimised, can help to achieve the same deformation with a reduced actuation force.In this paper, round corrugated panels are used in the compliant structure and the stiffness asymmetry is introduced by changing the geometry of the corrugation panel. A new equivalent model of the round corrugated panel is developed, which takes the axial and bending coupling of the corrugated panel into account. The stiffness matrix of the corrugated panel is obtained using the equivalent model, and then the deflections of the compliant structure can be calculated. The results are compared to those from detailed finite element models built in the commercial software Abaqus. Samples with different geometries were manufactured for experimental tests.After verifying the equivalent model, optimisation is performed to find the optimum geometries of the compliant structures. The actuation force of a single compliant structure is first optimised, and then the optimisation is performed for a compliant structure consisting of multiple units. A case study is used to show the performance improvement obtained. Journal Article The Aeronautical Journal 122 1249 442 461 Cambridge University Press 0001-9240 2059-6464 Morphing aircraft; compliant structure; corrugated panel; optimisation 31 3 2018 2018-03-31 10.1017/aer.2017.144 COLLEGE NANME Science and Engineering - Faculty COLLEGE CODE FGSEN Swansea University 2021-02-23T13:58:15.5325505 2018-02-19T12:15:05.4428890 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised C. Wang 1 H. H. Khodaparast 2 M. I. Friswell 3 A. D. Shaw 4 Michael Friswell 5 Hamed Haddad Khodaparast 0000-0002-3721-4980 6 Alexander Shaw 0000-0002-7521-827X 7 0038777-19022018132107.pdf wang2018.pdf 2018-02-19T13:21:07.1000000 Output 2243514 application/pdf Accepted Manuscript true 2018-07-14T00:00:00.0000000 true eng
title Compliant structures based on stiffness asymmetry
spellingShingle Compliant structures based on stiffness asymmetry
Michael Friswell
Hamed Haddad Khodaparast
Alexander Shaw
title_short Compliant structures based on stiffness asymmetry
title_full Compliant structures based on stiffness asymmetry
title_fullStr Compliant structures based on stiffness asymmetry
title_full_unstemmed Compliant structures based on stiffness asymmetry
title_sort Compliant structures based on stiffness asymmetry
author_id_str_mv 5894777b8f9c6e64bde3568d68078d40
f207b17edda9c4c3ea074cbb7555efc1
10cb5f545bc146fba9a542a1d85f2dea
author_id_fullname_str_mv 5894777b8f9c6e64bde3568d68078d40_***_Michael Friswell
f207b17edda9c4c3ea074cbb7555efc1_***_Hamed Haddad Khodaparast
10cb5f545bc146fba9a542a1d85f2dea_***_Alexander Shaw
author Michael Friswell
Hamed Haddad Khodaparast
Alexander Shaw
author2 C. Wang
H. H. Khodaparast
M. I. Friswell
A. D. Shaw
Michael Friswell
Hamed Haddad Khodaparast
Alexander Shaw
format Journal article
container_title The Aeronautical Journal
container_volume 122
container_issue 1249
container_start_page 442
publishDate 2018
institution Swansea University
issn 0001-9240
2059-6464
doi_str_mv 10.1017/aer.2017.144
publisher Cambridge University Press
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
document_store_str 1
active_str 0
description One of the key problems in the development of morphing aircraft is the morphing structure, which should be able to carry loads and change its geometry simultaneously. This paper investigates a compliant structure, which has the potential to change the dihedral angle of morphing wing-tip devices. The compliant structure is able to induce deformation by unsymmetrical stiffness allocation and carry aerodynamic loads if the total stiffness of the structure is sufficient.The concept has been introduced by building a simplified model of the structure and deriving the analytical equations. However, a properly designed stiffness asymmetry, which is optimised, can help to achieve the same deformation with a reduced actuation force.In this paper, round corrugated panels are used in the compliant structure and the stiffness asymmetry is introduced by changing the geometry of the corrugation panel. A new equivalent model of the round corrugated panel is developed, which takes the axial and bending coupling of the corrugated panel into account. The stiffness matrix of the corrugated panel is obtained using the equivalent model, and then the deflections of the compliant structure can be calculated. The results are compared to those from detailed finite element models built in the commercial software Abaqus. Samples with different geometries were manufactured for experimental tests.After verifying the equivalent model, optimisation is performed to find the optimum geometries of the compliant structures. The actuation force of a single compliant structure is first optimised, and then the optimisation is performed for a compliant structure consisting of multiple units. A case study is used to show the performance improvement obtained.
published_date 2018-03-31T03:49:10Z
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score 11.013731

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