DC Field | Value | Language |
---|---|---|
dc.contributor.author | 김대관 | ko |
dc.contributor.author | 배재성 | ko |
dc.contributor.author | 이인 | ko |
dc.contributor.author | 한재흥 | ko |
dc.date.accessioned | 2009-02-12T07:14:39Z | - |
dc.date.available | 2009-02-12T07:14:39Z | - |
dc.date.created | 2012-02-06 | - |
dc.date.created | 2012-02-06 | - |
dc.date.created | 2012-02-06 | - |
dc.date.issued | 2005-07 | - |
dc.identifier.citation | 한국소음진동공학회논문집, v.15, no.7, pp.813 - 820 | - |
dc.identifier.issn | 1598-2785 | - |
dc.identifier.uri | http://hdl.handle.net/10203/8493 | - |
dc.description.abstract | A deployable missile control fin has some structural nonlinearities because of the worn or loose hinges and the manufacturing tolerance. The structural nonlinearity cannot be eliminated completely, and exerts significant effects on the static and dynamic characteristics of the control fin. Thus, it is important to establish the accurate deployable missile control fin model. In the present study, the nonlinear dynamic model of the deployable missile control fin is developed using a substructure synthesis method. The deployable missile control fin can be subdivided into two substructures represented by linear dynamic models and a nonlinear hinge with structural nonlinearities. The nonlinear hinge model is established by using a system identification method, and the substructure modes are improved using the Frequency Response Method. A substructure synthesis method is expanded to couple the substructure models and the nonlinear hinge model, and the nonlinear dynamic model of the fin is developed. Finally, the established nonlinear dynamic model of the deployable missile control fin is verified by dynamic tests. The established model is in good agreement with test results, showing that the present approach is useful in aeroelastic stability analyses such as time-domain nonlinear flutter analysis. | - |
dc.language | Korean | - |
dc.language.iso | ko | en |
dc.publisher | 한국소음진동공학회 | - |
dc.title | 부구조물 합성법을 이용한 접는 미사일 조종날개 모델 수립 | - |
dc.title.alternative | Model Establishment of a Deployable Missile Control Fin Using Substructure Synthesis Method | - |
dc.type | Article | - |
dc.identifier.alternativecitation | Journal of The Korean Society for Noise and Vibratioin Engineering, v.15, no.7, pp.813-820 | en |
dc.publisher.alternative | The Korean Society for Noise and Vibration Engineering | en |
dc.subject.alternative | Missile Control Fin | en |
dc.subject.alternative | Substructure Systhesis Method | en |
dc.subject.alternative | Model Improvement | en |
dc.subject.alternative | Natural Frequency | en |
dc.subject.alternative | Mode Shape | en |
dc.type.rims | ART | - |
dc.citation.volume | 15 | - |
dc.citation.issue | 7 | - |
dc.citation.beginningpage | 813 | - |
dc.citation.endingpage | 820 | - |
dc.citation.publicationname | 한국소음진동공학회논문집 | - |
dc.identifier.kciid | ART001185297 | - |
dc.contributor.localauthor | 이인 | - |
dc.contributor.localauthor | 한재흥 | - |
dc.contributor.nonIdAuthor | 김대관 | - |
dc.contributor.nonIdAuthor | 배재성 | - |
dc.description.isOpenAccess | N | - |
dc.subject.keywordAuthor | Missile Control Fin | - |
dc.subject.keywordAuthor | Substructure Synthesis Method | - |
dc.subject.keywordAuthor | Model Improvement | - |
dc.subject.keywordAuthor | Natural Frequency | - |
dc.subject.keywordAuthor | Mode Shape | - |
dc.subject.keywordAuthor | 미사일 조종날개 | - |
dc.subject.keywordAuthor | 부구조물 합성법 | - |
dc.subject.keywordAuthor | 모델 개선 | - |
dc.subject.keywordAuthor | 고유주파수 | - |
dc.subject.keywordAuthor | 모드 형상 | - |
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