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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.
KSR-Ⅲ 조립모델 전기체 모드시험 및 비행모델 모드 해석
윤세현(S. H. Youn),장영순(Y. S. Jang),박순홍(S. H. Park),이영무(Y. M. Yi) 한국항공우주학회 2004 韓國航空宇宙學會誌 Vol.32 No.2
3단형 과학 로켓(KSR-Ⅲ)는 케로신과 액체산소를 연료로 하는 액체추진기관을 사용하는 과학로켓이다. 로켓의 구조는 엔진부, 탱크부와 탑재부의 부분조립체로 크게 나눌 수 있으며, 각 부분 조립체는 주로 알루미늄 구조로 제작된 부분체로 구성된다. 본 논문에서는 조립모델(EM) 전기체의 모드시험을 수행하였고 그 결과를 비행모델(FM) 모드 해석에 적용하여 동특성을 파악하였다. 조립모델 전기체의 동특성을 구하기 위해 모드시험시 번지스프링을 사용하여 자유경계조건을 부과하였고 2개의 가진기를 사용하여 다입력을 가하였다. 조립모델 시험 결과를 이용하여 비행모델 모드 해석을 수행, 동적 특성을 보정하였다. KSR-Ⅲ(Korea Sounding Rocket-Ⅲ) is a sounding rocket having a liquid-type motor which uses Kerosene and LOX as fuel. The structure of KSR-Ⅲ can be divided into engine section, tank section, and payload section. Each section is composed of several subsystems, which are mainly made of Aluminum.In this paper the procedure and the results of a modal test of KSR-Ⅲ EM (Engineering Model) are described. Using the results of modal test, modal analysis of KSR-Ⅲ FM(Flight Model) is performed. In order to get the dynamic properties of the whole structure of KSR-Ⅲ EM, a modal test was performed. In testing, KSR-Ⅲ was hung by bungee springs to establish free boundary conditions and multiple inputs were applied using 2 modal shakers. Modal test results are used for tuning the analytical model of KSR-Ⅲ FM.