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피칭운동을 하는 대형 우주발사체 형상의 천음속 비정상 유동해석
김동현(D. H. Kim),김요한(Y. H. Kim),김동환(D. H. Kim),윤세현(S. H. Yoon),김광수(G. S. Kim),장영순(Y. H. Jang),김수현(S. H. Kim) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.11
In this study, steady and unsteady aerodynamic analyses of a huge rocket configuration have been conducted in the transonic flow region. Launch vehicle structural response can couple with transonic flow state transitions at the nose of payload fairing. Before doing fluid-structure coupled transonic aeroealstic simulations for a huge rocket configuration, transonic aerodynamic characteristics are investigated for pitching motions of the rocket with angle-of attack. Unsteady CFD analysis method with moving grid technique based on Reynolds-averaged Navier-Stokes equations with κ-ω SST transition turbulence model is applied to accurately predict the transonic loads of the rocket with pitching motion. It is importantly shown that the fluctuated amplitude of lateral aerodynamic loads imposed on the rocket due to pitching motion can be significantly increased in the transonic region when the rocket has certain angle-of-attack.
피칭운동을 고려한 우주발사체 형상의 천음속 비정상 유동해석
김동현(D.H. Kim),김요한(Y.H. Kim),김동환(D.H. Kim),윤세현(S.H. Yoon),김광수(G.S. Kim),장영순(Y.H. Jang),김수현(S.H. Kim) 한국전산유체공학회 2011 한국전산유체공학회지 Vol.16 No.1
In this study, steady and unsteady aerodynamic analyses of a huge rocket configuration have been conducted in a transonic flow region. The launch vehicle structural response are coupled with the transonic flow state transitions at the nose of the payload fairing. Before performing the coupled fluid-structure transonic aeroealstic simulations transonic aerodynamic characteristics are investigated for the pitching motions of the rocket at finite angle-of-attack. An unsteady CFD analysis method with a moving grid technique based on the Reynolds-averaged Navier-Stokes equations with the k-w SST transition turbulence model is applied to accurately predict the transonic loads of the rocket at pitching motion. It is shown that the fluctuating amplitude of the lateral aerodynamic loads imposed on the rocket due to the pitching motion can be significantly increased in the transonic flow region.
김요한(Y.H. Kim),김동현(D.H. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
A new method identifies coupled fluid-structure system with a reduced set of state variables is presented. Assuming that the structural model is known a priori either from an analysis or a test and using linear transformations between structural and aeroelastic states, it is possible to deduce aerodynamic information from sampled time histories of the aeroelastic system. More specifically given a finite set of structural modes the method extracts generalized aerodynamic force matrix corresponding to these mode shapes. Once the aerodynamic forces are known, an aeroelastic reduced-order model can be constructed in discrete-time, state-space format by coupling the structural model and the aerodynamic system. The resulting reduced-order model is suitable for constant Mach, varying density analysis.