Flutter stability prediction using the unsteady aerodynamic reduced-order model = 비정상 공기력 축약 모델을 이용한 플러터 안정성 예측 연구

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CFD-base aeroelastic simulations are recognized as the most accurate schemes because they have significant advantages in terms of accuracy of nonlinear flow calculation especially in transonic and low supersonic regimes. However, in spite of their accuracy, application of this approach to an actual aircraft model is extremely time consuming. Moreover, because the aeroelastic instabilities can only be predicted by simulating whether the response is decaying or diverging, the aeroelastic analysis should be conducted several times until the neutral response is found. Therefore, to overcome these difficulties, this paper has introduced an efficient aeroelastic analysis methodology based on reduced-order modeling (ROM), whereby unsteady aerodynamic forces are determined without direct aerodynamic computations. In this study, two reduced-order models (ROM) for unsteady aerodynamics are formulated and the aeroelastic analysis codes using the ROM were developed. System identification and proper orthogonal decomposition (POD) methods are applied to construct the reduced order models of unsteady aerodynamics. In the system identification approach, the aerodynamic system is considered as a black box and the modal responses and generalized aerodynamic signals are captured to construct the Auto Regressive Moving Average (ARMA) model. This model offers full information of the relationship between the wing motion and the unsteady aerodynamic loads in the aeroelastic analysis instead of the aerodynamic solver. This approach is very simple and significantly faster than the CFD-based aeroelastic analysis. However, it shows distinct limitation when the aerodynamic system has an uncertainty, such as control surface motion. In the POD method, the aerodynamic system is projected into a K-L basis or optimal basis set. Thus the aerodynamic system can be expressed by the modal superposition such that the deformation of the structure can be described by a linear combination of these mod...
Advisors
Lee, Inresearcher이인researcher
Description
한국과학기술원 : 항공우주공학전공,
Publisher
한국과학기술원
Issue Date
2005
Identifier
244813/325007  / 020005803
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학전공, 2005.2, [ xi, 177 p. ]

Keywords

navier-stokes; euler; transonic small disturbance theory; system identification; proper orthogonal decomposition; reduced-order modeling; aeroelasticity; transonic flutter; control surface; 조종면; 나비에스토크스; 오일러; 천음속 미소교란 방정식; 시스템 판별법; 적정직교분해; 천음속 플러터; 공력탄성학; 축약모델

URI
http://hdl.handle.net/10203/26320
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=244813&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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