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Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force

M Rezaei, SA Fazelzadeh, A Mazidi, H Haddad Khodaparast, Hamed Haddad Khodaparast Orcid Logo

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Start page: 095441001877389

Swansea University Author: Hamed Haddad Khodaparast Orcid Logo

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DOI (Published version): 10.1177/0954410018773898

Abstract

In this study, flutter uncertainty analysis of an aircraft wing subjected to a thrust force is investigated using fuzzy method. The linear wing model contains bending and torsional flexibility and the engine is considered as a rigid external mass with thrust force. Peters’ unsteady thin airfoil theo...

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Published in: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
ISSN: 0954-4100 2041-3025
Published: 2018
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URI: https://cronfa.swan.ac.uk/Record/cronfa40560
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first_indexed 2018-06-04T13:18:07Z
last_indexed 2018-09-04T12:54:35Z
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spelling 2018-09-04T10:32:56.5948680 v2 40560 2018-06-04 Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force f207b17edda9c4c3ea074cbb7555efc1 0000-0002-3721-4980 Hamed Haddad Khodaparast Hamed Haddad Khodaparast true false 2018-06-04 AERO In this study, flutter uncertainty analysis of an aircraft wing subjected to a thrust force is investigated using fuzzy method. The linear wing model contains bending and torsional flexibility and the engine is considered as a rigid external mass with thrust force. Peters’ unsteady thin airfoil theory is used to model the aerodynamic loading. The aeroelastic governing equations are derived based on Hamilton’s principle and converted to a set of ordinary differential equations using Galerkin method. In the flutter analysis, it is assumed that the wing static deflections do not have influence on the results. The wing bending and torsional rigidity, aerodynamic lift curve slope and air density are considered as uncertain parameters and modelled as triangle and trapezium membership functions. The eigenvalue problem with fuzzy input parameters is solved using fuzzy Taylor expansion method and a sensitivity analysis is performed. Also, the upper and lower bounds of flutter region at different α-cuts are extracted. Results show that this method is a low-cost method with reasonable accuracy to estimate the flutter speed and frequency in the presence of uncertainties. Journal Article Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 095441001877389 0954-4100 2041-3025 Uncertainty, flutter, aircraft wing, thrust force, fuzzy method, non-probabilistic 31 12 2018 2018-12-31 10.1177/0954410018773898 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University 2018-09-04T10:32:56.5948680 2018-06-04T10:16:23.6876460 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering M Rezaei 1 SA Fazelzadeh 2 A Mazidi 3 H Haddad Khodaparast 4 Hamed Haddad Khodaparast 0000-0002-3721-4980 5 0040560-12062018083553.pdf rezaei2018.pdf 2018-06-12T08:35:53.3370000 Output 5814570 application/pdf Accepted Manuscript true 2018-06-12T00:00:00.0000000 true eng
title Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force
spellingShingle Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force
Hamed Haddad Khodaparast
title_short Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force
title_full Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force
title_fullStr Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force
title_full_unstemmed Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force
title_sort Fuzzy uncertainty analysis in the flutter boundary of an aircraft wing subjected to a thrust force
author_id_str_mv f207b17edda9c4c3ea074cbb7555efc1
author_id_fullname_str_mv f207b17edda9c4c3ea074cbb7555efc1_***_Hamed Haddad Khodaparast
author Hamed Haddad Khodaparast
author2 M Rezaei
SA Fazelzadeh
A Mazidi
H Haddad Khodaparast
Hamed Haddad Khodaparast
format Journal article
container_title Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
container_start_page 095441001877389
publishDate 2018
institution Swansea University
issn 0954-4100
2041-3025
doi_str_mv 10.1177/0954410018773898
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 Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
document_store_str 1
active_str 0
description In this study, flutter uncertainty analysis of an aircraft wing subjected to a thrust force is investigated using fuzzy method. The linear wing model contains bending and torsional flexibility and the engine is considered as a rigid external mass with thrust force. Peters’ unsteady thin airfoil theory is used to model the aerodynamic loading. The aeroelastic governing equations are derived based on Hamilton’s principle and converted to a set of ordinary differential equations using Galerkin method. In the flutter analysis, it is assumed that the wing static deflections do not have influence on the results. The wing bending and torsional rigidity, aerodynamic lift curve slope and air density are considered as uncertain parameters and modelled as triangle and trapezium membership functions. The eigenvalue problem with fuzzy input parameters is solved using fuzzy Taylor expansion method and a sensitivity analysis is performed. Also, the upper and lower bounds of flutter region at different α-cuts are extracted. Results show that this method is a low-cost method with reasonable accuracy to estimate the flutter speed and frequency in the presence of uncertainties.
published_date 2018-12-31T03:51:37Z
_version_ 1763752539690369024
score 11.016235

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