Nonlinear modal interactions in composite thin-walled beam structures with simultaneous 1:2 internal and 1:1 external resonances
Nonlinear dynamic characteristics of a composite aircraft wing structure modeled by a geometrically nonlinear anisotropic thin-walled beam in the presence of simultaneous 1:2 internal and 1:1 external resonances are investigated. Some prominent non-classical effects such as of transverse shear strai...
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| Veröffentlicht in: | Nonlinear dynamics 2016-10, Vol.86 (2), p.1381-1405 |
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| creator | Wang, Xiao Qin, Zhanming |
| description | Nonlinear dynamic characteristics of a composite aircraft wing structure modeled by a geometrically nonlinear anisotropic thin-walled beam in the presence of simultaneous 1:2 internal and 1:1 external resonances are investigated. Some prominent non-classical effects such as of transverse shear strain, warping inhibition, and three-dimensional strain are considered in the beam model. Moreover, circumferentially asymmetric stiffness lay-up configuration is adapted to generate the transverse bending-twisting elastic coupling. The solution methodology is based on the Extended Galerkin’s Method, and the method of multiple scales is applied to the system in order to obtain the equations of amplitude and modulation. Steady-state solutions and their stability are investigated. The peculiarity of the internal resonances and the conditions for saturation and jump phenomenon during the modal interactions are discussed and the commercial code ABAQUS is used to validate the theoretical results we have obtained. Finally, the prominent features of modal interactions in composite thin-walled beam structures are summarized and pertinent suggestions concerning safe design of the wing structures are given. |
| doi_str_mv | 10.1007/s11071-016-2970-3 |
| format | Article |
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Some prominent non-classical effects such as of transverse shear strain, warping inhibition, and three-dimensional strain are considered in the beam model. Moreover, circumferentially asymmetric stiffness lay-up configuration is adapted to generate the transverse bending-twisting elastic coupling. The solution methodology is based on the Extended Galerkin’s Method, and the method of multiple scales is applied to the system in order to obtain the equations of amplitude and modulation. Steady-state solutions and their stability are investigated. The peculiarity of the internal resonances and the conditions for saturation and jump phenomenon during the modal interactions are discussed and the commercial code ABAQUS is used to validate the theoretical results we have obtained. Finally, the prominent features of modal interactions in composite thin-walled beam structures are summarized and pertinent suggestions concerning safe design of the wing structures are given.</description><identifier>ISSN: 0924-090X</identifier><identifier>EISSN: 1573-269X</identifier><identifier>DOI: 10.1007/s11071-016-2970-3</identifier><language>eng</language><publisher>Dordrecht: Springer Netherlands</publisher><subject>Anisotropy ; Automotive Engineering ; Beams (structural) ; Classical Mechanics ; Computer simulation ; Control ; Dynamic characteristics ; Dynamical Systems ; Engineering ; Finite element method ; Galerkin method ; Galerkin methods ; Lay-up ; Mathematical models ; Mechanical Engineering ; Method of multiple scales ; Multiscale analysis ; Nonlinear dynamics ; Nonlinearity ; Original Paper ; Shear strain ; Stiffness ; Three dimensional models ; Twisting ; Vibration ; Wings (aircraft)</subject><ispartof>Nonlinear dynamics, 2016-10, Vol.86 (2), p.1381-1405</ispartof><rights>Springer Science+Business Media Dordrecht 2016</rights><rights>Copyright Springer Science & Business Media 2016</rights><rights>Nonlinear Dynamics is a copyright of Springer, (2016). All Rights Reserved.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c377t-ee8127472d2435f000dfbbead9aea7c34b115dbfcb88bd505373d39428d39b923</citedby><cites>FETCH-LOGICAL-c377t-ee8127472d2435f000dfbbead9aea7c34b115dbfcb88bd505373d39428d39b923</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktopdf>$$Uhttps://link.springer.com/content/pdf/10.1007/s11071-016-2970-3$$EPDF$$P50$$Gspringer$$H</linktopdf><linktohtml>$$Uhttps://link.springer.com/10.1007/s11071-016-2970-3$$EHTML$$P50$$Gspringer$$H</linktohtml><link.rule.ids>314,776,780,27903,27904,41467,42536,51297</link.rule.ids></links><search><creatorcontrib>Wang, Xiao</creatorcontrib><creatorcontrib>Qin, Zhanming</creatorcontrib><title>Nonlinear modal interactions in composite thin-walled beam structures with simultaneous 1:2 internal and 1:1 external resonances</title><title>Nonlinear dynamics</title><addtitle>Nonlinear Dyn</addtitle><description>Nonlinear dynamic characteristics of a composite aircraft wing structure modeled by a geometrically nonlinear anisotropic thin-walled beam in the presence of simultaneous 1:2 internal and 1:1 external resonances are investigated. Some prominent non-classical effects such as of transverse shear strain, warping inhibition, and three-dimensional strain are considered in the beam model. Moreover, circumferentially asymmetric stiffness lay-up configuration is adapted to generate the transverse bending-twisting elastic coupling. The solution methodology is based on the Extended Galerkin’s Method, and the method of multiple scales is applied to the system in order to obtain the equations of amplitude and modulation. Steady-state solutions and their stability are investigated. The peculiarity of the internal resonances and the conditions for saturation and jump phenomenon during the modal interactions are discussed and the commercial code ABAQUS is used to validate the theoretical results we have obtained. Finally, the prominent features of modal interactions in composite thin-walled beam structures are summarized and pertinent suggestions concerning safe design of the wing structures are given.</description><subject>Anisotropy</subject><subject>Automotive Engineering</subject><subject>Beams (structural)</subject><subject>Classical Mechanics</subject><subject>Computer simulation</subject><subject>Control</subject><subject>Dynamic characteristics</subject><subject>Dynamical Systems</subject><subject>Engineering</subject><subject>Finite element method</subject><subject>Galerkin method</subject><subject>Galerkin methods</subject><subject>Lay-up</subject><subject>Mathematical models</subject><subject>Mechanical Engineering</subject><subject>Method of multiple scales</subject><subject>Multiscale analysis</subject><subject>Nonlinear dynamics</subject><subject>Nonlinearity</subject><subject>Original Paper</subject><subject>Shear strain</subject><subject>Stiffness</subject><subject>Three dimensional models</subject><subject>Twisting</subject><subject>Vibration</subject><subject>Wings (aircraft)</subject><issn>0924-090X</issn><issn>1573-269X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2016</creationdate><recordtype>article</recordtype><sourceid>AFKRA</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><recordid>eNp9kUFrFTEUhYMo-Kz-AHcBN25ib5KZlxl3UlpbKHWj0F3IJHdsykzymmSo7vzpZpguSqHd3HBvzvk4cAj5yOELB1DHmXNQnAHfM9ErYPIV2fFWSSb2_fVrsoNeNAx6uH5L3uV8CwBSQLcj_65imHxAk-gcnZmoDwWTscXHkOtCbZwPMfuCtNz4wO7NNKGjA5qZ5pIWW5aEmd77ckOzn5epmIBxyZR_FRsrVKgJrh44xT8Ph-qJwQSL-T15M5op44eH94j8Ojv9eXLOLn98vzj5dsmsVKowxI4L1SjhRCPbseZ341BTuN6gUVY2A-etG0Y7dN3gWmilkk72jejqHHohj8jnjXtI8W7BXPTss8Vp2vJq3nUAQgrRVumnJ9LbuKyxs67ffVPZTfOSamV1Suz3sqr4prIp5pxw1IfkZ5P-ag56bU5vzenanF6b06tHbJ5cteE3pkfkZ03_ASQlnGY</recordid><startdate>20161001</startdate><enddate>20161001</enddate><creator>Wang, Xiao</creator><creator>Qin, Zhanming</creator><general>Springer Netherlands</general><general>Springer Nature B.V</general><scope>AAYXX</scope><scope>CITATION</scope><scope>8FE</scope><scope>8FG</scope><scope>ABJCF</scope><scope>AFKRA</scope><scope>BENPR</scope><scope>BGLVJ</scope><scope>CCPQU</scope><scope>DWQXO</scope><scope>HCIFZ</scope><scope>L6V</scope><scope>M7S</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PRINS</scope><scope>PTHSS</scope><scope>7SC</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>JQ2</scope><scope>KR7</scope><scope>L7M</scope><scope>L~C</scope><scope>L~D</scope></search><sort><creationdate>20161001</creationdate><title>Nonlinear modal interactions in composite thin-walled beam structures with simultaneous 1:2 internal and 1:1 external resonances</title><author>Wang, Xiao ; Qin, Zhanming</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c377t-ee8127472d2435f000dfbbead9aea7c34b115dbfcb88bd505373d39428d39b923</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2016</creationdate><topic>Anisotropy</topic><topic>Automotive Engineering</topic><topic>Beams (structural)</topic><topic>Classical Mechanics</topic><topic>Computer simulation</topic><topic>Control</topic><topic>Dynamic characteristics</topic><topic>Dynamical Systems</topic><topic>Engineering</topic><topic>Finite element method</topic><topic>Galerkin method</topic><topic>Galerkin methods</topic><topic>Lay-up</topic><topic>Mathematical models</topic><topic>Mechanical Engineering</topic><topic>Method of multiple scales</topic><topic>Multiscale analysis</topic><topic>Nonlinear dynamics</topic><topic>Nonlinearity</topic><topic>Original Paper</topic><topic>Shear strain</topic><topic>Stiffness</topic><topic>Three dimensional models</topic><topic>Twisting</topic><topic>Vibration</topic><topic>Wings (aircraft)</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Wang, Xiao</creatorcontrib><creatorcontrib>Qin, Zhanming</creatorcontrib><collection>CrossRef</collection><collection>ProQuest SciTech Collection</collection><collection>ProQuest Technology Collection</collection><collection>Materials Science & Engineering Collection</collection><collection>ProQuest Central UK/Ireland</collection><collection>ProQuest Central</collection><collection>Technology Collection</collection><collection>ProQuest One Community College</collection><collection>ProQuest Central Korea</collection><collection>SciTech Premium Collection</collection><collection>ProQuest Engineering Collection</collection><collection>Engineering Database</collection><collection>ProQuest One Academic Eastern Edition (DO NOT USE)</collection><collection>ProQuest One Academic</collection><collection>ProQuest One Academic UKI Edition</collection><collection>ProQuest Central China</collection><collection>Engineering Collection</collection><collection>Computer and Information Systems Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>ProQuest Computer Science Collection</collection><collection>Civil Engineering Abstracts</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Computer and Information Systems Abstracts Academic</collection><collection>Computer and Information Systems Abstracts Professional</collection><jtitle>Nonlinear dynamics</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Wang, Xiao</au><au>Qin, Zhanming</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Nonlinear modal interactions in composite thin-walled beam structures with simultaneous 1:2 internal and 1:1 external resonances</atitle><jtitle>Nonlinear dynamics</jtitle><stitle>Nonlinear Dyn</stitle><date>2016-10-01</date><risdate>2016</risdate><volume>86</volume><issue>2</issue><spage>1381</spage><epage>1405</epage><pages>1381-1405</pages><issn>0924-090X</issn><eissn>1573-269X</eissn><abstract>Nonlinear dynamic characteristics of a composite aircraft wing structure modeled by a geometrically nonlinear anisotropic thin-walled beam in the presence of simultaneous 1:2 internal and 1:1 external resonances are investigated. Some prominent non-classical effects such as of transverse shear strain, warping inhibition, and three-dimensional strain are considered in the beam model. Moreover, circumferentially asymmetric stiffness lay-up configuration is adapted to generate the transverse bending-twisting elastic coupling. The solution methodology is based on the Extended Galerkin’s Method, and the method of multiple scales is applied to the system in order to obtain the equations of amplitude and modulation. Steady-state solutions and their stability are investigated. The peculiarity of the internal resonances and the conditions for saturation and jump phenomenon during the modal interactions are discussed and the commercial code ABAQUS is used to validate the theoretical results we have obtained. Finally, the prominent features of modal interactions in composite thin-walled beam structures are summarized and pertinent suggestions concerning safe design of the wing structures are given.</abstract><cop>Dordrecht</cop><pub>Springer Netherlands</pub><doi>10.1007/s11071-016-2970-3</doi><tpages>25</tpages></addata></record> |
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| subjects | Anisotropy Automotive Engineering Beams (structural) Classical Mechanics Computer simulation Control Dynamic characteristics Dynamical Systems Engineering Finite element method Galerkin method Galerkin methods Lay-up Mathematical models Mechanical Engineering Method of multiple scales Multiscale analysis Nonlinear dynamics Nonlinearity Original Paper Shear strain Stiffness Three dimensional models Twisting Vibration Wings (aircraft) |
| title | Nonlinear modal interactions in composite thin-walled beam structures with simultaneous 1:2 internal and 1:1 external resonances |
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