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Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling

Javad Taghipour, Jiaying Zhang, Alexander Shaw Orcid Logo, Michael Friswell, Huayuan Gu, Chen Wang

Nonlinear Dynamics, Volume: 107, Issue: 1, Pages: 617 - 639

Swansea University Authors: Javad Taghipour, Alexander Shaw Orcid Logo, Michael Friswell

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DOI (Published version): 10.1007/s11071-021-07067-x

Abstract

With increasing demand for rotor blades in engineering applications, improving the performance of such structures using morphing blades has received considerable attention. Resonant passive energy balancing (RPEB) is a relatively new concept introduced to minimize the required actuation energy. This...

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Published in: Nonlinear Dynamics
ISSN: 0924-090X 1573-269X
Published: Springer Science and Business Media LLC 2022
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URI: https://cronfa.swan.ac.uk/Record/cronfa59135
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Resonant passive energy balancing (RPEB) is a relatively new concept introduced to minimize the required actuation energy. This study investigates RPEB in morphing helicopter blades with lag&#x2013;twist coupling. The structure of a rotating blade with a moving mass at the tip is considered under aerodynamic loading. To this end, a three-degree-of-freedom (3DOF) reduced-order model is used to analyse and understand the complicated nonlinear aeroelastic behaviour of the structure. This model includes the pitch angle and lagging of the blade, along with the motion of the moving mass. First, the 3DOF model is simplified to a single-degree-of-freedom model for the pitch angle dynamics of the blade to examine the effect of important parameters on the pitch response. The results demonstrate that the coefficient of lag&#x2013;twist coupling and the direction of aerodynamic moment on the blade are two parameters that play important roles in controlling the pitch angle, particularly the phase. Then, neglecting the aerodynamic forces, the 3DOF system is studied to investigate the sensitivity of its dynamics to changes in the parameters of the system. The results of the structural analysis can be used to tune the parameters of the blade in order to use the resonant energy of the structure and to reduce the required actuation force. A sensitivity analysis is then performed on the dynamics of the 3DOF model in the presence of aerodynamic forces to investigate the controllability of the amplitude and phase of the pitch angle. The results show that the bend&#x2013;twist coupling and the distance between the aerodynamic centre and the rotation centre (representing the direction and magnitude of aerodynamic moments) play significant roles in determining the pitch dynamics.</abstract><type>Journal Article</type><journal>Nonlinear Dynamics</journal><volume>107</volume><journalNumber>1</journalNumber><paginationStart>617</paginationStart><paginationEnd>639</paginationEnd><publisher>Springer Science and Business Media LLC</publisher><placeOfPublication/><isbnPrint/><isbnElectronic/><issnPrint>0924-090X</issnPrint><issnElectronic>1573-269X</issnElectronic><keywords>Helicopter blade morphing, Resonant passive energy balancing, Bend&#x2013;twist coupling, Inertial morphing</keywords><publishedDay>1</publishedDay><publishedMonth>1</publishedMonth><publishedYear>2022</publishedYear><publishedDate>2022-01-01</publishedDate><doi>10.1007/s11071-021-07067-x</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>SU Library paid the OA fee (TA Institutional Deal)</apcterm><funders>European Commission under the European Union&#x2019;s Horizon 2020 Framework Programme &#x2018;Shape Adaptive Blades for Rotorcraft Efficiency&#x2019; Grant Agreement 723491.</funders><lastEdited>2022-01-18T16:12:04.4795548</lastEdited><Created>2022-01-10T15:35:57.8600206</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>Javad</firstname><surname>Taghipour</surname><order>1</order></author><author><firstname>Jiaying</firstname><surname>Zhang</surname><order>2</order></author><author><firstname>Alexander</firstname><surname>Shaw</surname><orcid>0000-0002-7521-827X</orcid><order>3</order></author><author><firstname>Michael</firstname><surname>Friswell</surname><order>4</order></author><author><firstname>Huayuan</firstname><surname>Gu</surname><order>5</order></author><author><firstname>Chen</firstname><surname>Wang</surname><order>6</order></author></authors><documents><document><filename>59135__22099__29e87eefa1d548abb2b7ab5928a54d6b.pdf</filename><originalFilename>11071_2021_Article_7067.pdf</originalFilename><uploaded>2022-01-10T15:35:57.8597747</uploaded><type>Output</type><contentLength>6368591</contentLength><contentType>application/pdf</contentType><version>Version of Record</version><cronfaStatus>true</cronfaStatus><documentNotes>This article is licensed under a Creative Commons Attribution 4.0 International License, which permits use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons licence, and indicate if changes were made.</documentNotes><copyrightCorrect>true</copyrightCorrect><language>eng</language><licence>http://creativecommons.org/licenses/by/4.0/</licence></document></documents><OutputDurs/></rfc1807>
spelling 2022-01-18T16:12:04.4795548 v2 59135 2022-01-10 Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling dc7cba835218dde37fe7f447962d4058 Javad Taghipour Javad Taghipour true false 10cb5f545bc146fba9a542a1d85f2dea 0000-0002-7521-827X Alexander Shaw Alexander Shaw true false 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 2022-01-10 FGSEN With increasing demand for rotor blades in engineering applications, improving the performance of such structures using morphing blades has received considerable attention. Resonant passive energy balancing (RPEB) is a relatively new concept introduced to minimize the required actuation energy. This study investigates RPEB in morphing helicopter blades with lag–twist coupling. The structure of a rotating blade with a moving mass at the tip is considered under aerodynamic loading. To this end, a three-degree-of-freedom (3DOF) reduced-order model is used to analyse and understand the complicated nonlinear aeroelastic behaviour of the structure. This model includes the pitch angle and lagging of the blade, along with the motion of the moving mass. First, the 3DOF model is simplified to a single-degree-of-freedom model for the pitch angle dynamics of the blade to examine the effect of important parameters on the pitch response. The results demonstrate that the coefficient of lag–twist coupling and the direction of aerodynamic moment on the blade are two parameters that play important roles in controlling the pitch angle, particularly the phase. Then, neglecting the aerodynamic forces, the 3DOF system is studied to investigate the sensitivity of its dynamics to changes in the parameters of the system. The results of the structural analysis can be used to tune the parameters of the blade in order to use the resonant energy of the structure and to reduce the required actuation force. A sensitivity analysis is then performed on the dynamics of the 3DOF model in the presence of aerodynamic forces to investigate the controllability of the amplitude and phase of the pitch angle. The results show that the bend–twist coupling and the distance between the aerodynamic centre and the rotation centre (representing the direction and magnitude of aerodynamic moments) play significant roles in determining the pitch dynamics. Journal Article Nonlinear Dynamics 107 1 617 639 Springer Science and Business Media LLC 0924-090X 1573-269X Helicopter blade morphing, Resonant passive energy balancing, Bend–twist coupling, Inertial morphing 1 1 2022 2022-01-01 10.1007/s11071-021-07067-x COLLEGE NANME Science and Engineering - Faculty COLLEGE CODE FGSEN Swansea University SU Library paid the OA fee (TA Institutional Deal) European Commission under the European Union’s Horizon 2020 Framework Programme ‘Shape Adaptive Blades for Rotorcraft Efficiency’ Grant Agreement 723491. 2022-01-18T16:12:04.4795548 2022-01-10T15:35:57.8600206 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised Javad Taghipour 1 Jiaying Zhang 2 Alexander Shaw 0000-0002-7521-827X 3 Michael Friswell 4 Huayuan Gu 5 Chen Wang 6 59135__22099__29e87eefa1d548abb2b7ab5928a54d6b.pdf 11071_2021_Article_7067.pdf 2022-01-10T15:35:57.8597747 Output 6368591 application/pdf Version of Record true This article is licensed under a Creative Commons Attribution 4.0 International License, which permits use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons licence, and indicate if changes were made. true eng http://creativecommons.org/licenses/by/4.0/
title Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling
spellingShingle Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling
Javad Taghipour
Alexander Shaw
Michael Friswell
title_short Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling
title_full Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling
title_fullStr Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling
title_full_unstemmed Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling
title_sort Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling
author_id_str_mv dc7cba835218dde37fe7f447962d4058
10cb5f545bc146fba9a542a1d85f2dea
5894777b8f9c6e64bde3568d68078d40
author_id_fullname_str_mv dc7cba835218dde37fe7f447962d4058_***_Javad Taghipour
10cb5f545bc146fba9a542a1d85f2dea_***_Alexander Shaw
5894777b8f9c6e64bde3568d68078d40_***_Michael Friswell
author Javad Taghipour
Alexander Shaw
Michael Friswell
author2 Javad Taghipour
Jiaying Zhang
Alexander Shaw
Michael Friswell
Huayuan Gu
Chen Wang
format Journal article
container_title Nonlinear Dynamics
container_volume 107
container_issue 1
container_start_page 617
publishDate 2022
institution Swansea University
issn 0924-090X
1573-269X
doi_str_mv 10.1007/s11071-021-07067-x
publisher Springer Science and Business Media LLC
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 With increasing demand for rotor blades in engineering applications, improving the performance of such structures using morphing blades has received considerable attention. Resonant passive energy balancing (RPEB) is a relatively new concept introduced to minimize the required actuation energy. This study investigates RPEB in morphing helicopter blades with lag–twist coupling. The structure of a rotating blade with a moving mass at the tip is considered under aerodynamic loading. To this end, a three-degree-of-freedom (3DOF) reduced-order model is used to analyse and understand the complicated nonlinear aeroelastic behaviour of the structure. This model includes the pitch angle and lagging of the blade, along with the motion of the moving mass. First, the 3DOF model is simplified to a single-degree-of-freedom model for the pitch angle dynamics of the blade to examine the effect of important parameters on the pitch response. The results demonstrate that the coefficient of lag–twist coupling and the direction of aerodynamic moment on the blade are two parameters that play important roles in controlling the pitch angle, particularly the phase. Then, neglecting the aerodynamic forces, the 3DOF system is studied to investigate the sensitivity of its dynamics to changes in the parameters of the system. The results of the structural analysis can be used to tune the parameters of the blade in order to use the resonant energy of the structure and to reduce the required actuation force. A sensitivity analysis is then performed on the dynamics of the 3DOF model in the presence of aerodynamic forces to investigate the controllability of the amplitude and phase of the pitch angle. The results show that the bend–twist coupling and the distance between the aerodynamic centre and the rotation centre (representing the direction and magnitude of aerodynamic moments) play significant roles in determining the pitch dynamics.
published_date 2022-01-01T04:16:12Z
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score 10.997933

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