DC Field | Value | Language |
---|---|---|
dc.contributor.author | 유재한 | ko |
dc.contributor.author | 김동현 | ko |
dc.contributor.author | 권혁준 | ko |
dc.contributor.author | 이인 | ko |
dc.contributor.author | 백승길 | ko |
dc.contributor.author | 김영익 | ko |
dc.date.accessioned | 2013-03-03T22:47:48Z | - |
dc.date.available | 2013-03-03T22:47:48Z | - |
dc.date.created | 2012-02-06 | - |
dc.date.created | 2012-02-06 | - |
dc.date.issued | 2002-04 | - |
dc.identifier.citation | 한국군사과학기술학회지, v.5, no.4, pp.81 - 87 | - |
dc.identifier.issn | 1598-9127 | - |
dc.identifier.uri | http://hdl.handle.net/10203/80788 | - |
dc.description.abstract | In this paper, the transonic aeroelastic behavior of the generic fighter model is investigated in the time domain. The simulation of flutter flight test using forced harmonic motion of control surfaces including inertial coupling effects is conducted at the various conditions. The nonlinear aerodynamic effects are considered using a transonic small disturbance equation. A modal model obtained by a free vibration analysis is used for the structural model. The relations between the computed flutter boundary and the simulation results of the responses using the harmonic motions of control surfaces at various conditions are investigated. | - |
dc.language | Korean | - |
dc.publisher | 한국군사과학기술학회 | - |
dc.title | 항공기의 조종면 진동시 비선형 공탄성 시뮬레이션 | - |
dc.title.alternative | Nonlinear Aeroelastic Simulation of a Full-Span Aircraft with Oscillating Control Surfaces | - |
dc.type | Article | - |
dc.type.rims | ART | - |
dc.citation.volume | 5 | - |
dc.citation.issue | 4 | - |
dc.citation.beginningpage | 81 | - |
dc.citation.endingpage | 87 | - |
dc.citation.publicationname | 한국군사과학기술학회지 | - |
dc.contributor.localauthor | 이인 | - |
dc.contributor.nonIdAuthor | 유재한 | - |
dc.contributor.nonIdAuthor | 김동현 | - |
dc.contributor.nonIdAuthor | 권혁준 | - |
dc.contributor.nonIdAuthor | 백승길 | - |
dc.contributor.nonIdAuthor | 김영익 | - |
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