DC Field | Value | Language |
---|---|---|
dc.contributor.author | Bae, JS | ko |
dc.contributor.author | Lee, In | ko |
dc.date.accessioned | 2008-07-10T05:33:21Z | - |
dc.date.available | 2008-07-10T05:33:21Z | - |
dc.date.created | 2012-02-06 | - |
dc.date.created | 2012-02-06 | - |
dc.date.issued | 2004-01 | - |
dc.identifier.citation | JOURNAL OF SOUND AND VIBRATION, v.269, no.3-5, pp.669 - 687 | - |
dc.identifier.issn | 0022-460X | - |
dc.identifier.uri | http://hdl.handle.net/10203/5583 | - |
dc.description.abstract | Non-linear aeroelastic characteristics of a deployable missile control fin with structural non-linearity are investigated. A deployable missile control fin is modelled as a two-dimensional typical section model. Doublet-point method is used for the calculation of supersonic unsteady aerodynamic forces, and aerodynamic forces are approximated by using the minimum-state approximation. For non-linear flutter analysis structural non-linearity is represented by an asymmetric bilinear spring and is linearized by using the describing function method. The linear and non-linear flutter analyses indicate that the flutter characteristics are significantly dependent on the frequency ratio. From the non-linear flutter analysis, various types of limit cycle oscillations are observed in a wide range of air speeds below or above the linear divergent flutter boundary. The non-linear flutter characteristics and the non-linear aeroelastic responses are investigated. (C) 2003 Elsevier Ltd. All rights reserved. | - |
dc.description.sponsorship | This research was supported by Agency for Defense Development (ADD) and the Ministry of Science and Technology (National Research Laboratory Program) in the Republic of Korea. This support is gratefully acknowledged. | en |
dc.language | English | - |
dc.language.iso | en_US | en |
dc.publisher | ACADEMIC PRESS LTD ELSEVIER SCIENCE LTD | - |
dc.subject | CONTROL SURFACE FREEPLAY | - |
dc.subject | AEROELASTIC ANALYSIS | - |
dc.subject | FLUTTER ANALYSIS | - |
dc.subject | AIRFOIL SECTION | - |
dc.subject | BEHAVIOR | - |
dc.title | Limit cycle oscillation of missile control fin with structural non-linearity | - |
dc.type | Article | - |
dc.identifier.wosid | 000188195100013 | - |
dc.identifier.scopusid | 2-s2.0-0346500813 | - |
dc.type.rims | ART | - |
dc.citation.volume | 269 | - |
dc.citation.issue | 3-5 | - |
dc.citation.beginningpage | 669 | - |
dc.citation.endingpage | 687 | - |
dc.citation.publicationname | JOURNAL OF SOUND AND VIBRATION | - |
dc.embargo.liftdate | 9999-12-31 | - |
dc.embargo.terms | 9999-12-31 | - |
dc.contributor.localauthor | Lee, In | - |
dc.contributor.nonIdAuthor | Bae, JS | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordPlus | CONTROL SURFACE FREEPLAY | - |
dc.subject.keywordPlus | AEROELASTIC ANALYSIS | - |
dc.subject.keywordPlus | FLUTTER ANALYSIS | - |
dc.subject.keywordPlus | AIRFOIL SECTION | - |
dc.subject.keywordPlus | BEHAVIOR | - |
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