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극소형 위성발사를 위한 공중발사 로켓 미리내Ⅱ의 시스템 설계
이영재(Y-J Lee),김진호(J-H Kim),최영창(Y-C Choi),이재우(J-W Lee),변영환(Y-H Byun),이창진(C. Lee) 한국항공우주학회 2005 韓國航空宇宙學會誌 Vol.33 No.12
최근 활발한 연구가 진행 중인 공중발사 방식은 극소형 위성을 매우 저렴한 비용으로 발사할 수 있는 효율적인 방법이다. 본 연구에서는 비교적 단순한 임무를 수행할 수 있는 나노 위성을 공중발사 방식을 이용하여 원 궤도에 올릴 수 있는 공중발사 로켓 시스템설계와 각 단별 계통 설계를 수행하였다. 이를 위하여 공중발사 로켓 시스템의 WBS와 각 계통별 작동개념도를 정립하였고, 이를 바탕으로 시스템 세부형상과 DMU를 구현하였다. Air-Launching is an effective method that can launch the 'Nanosat' with low launching cost. In this study, system and subsystem design of the air launching rocket for nanosats which perform a simple mission, have been performed. For this purpose, the WBS of the MIRINAEⅡ, and the subsystem schematics have been defined first. Based on these results, detailed configuration and DMU have been developed.
초음속 고받음각에서의 원뿔형 물체 주위의 비대칭 와류 특성 연구
박미영(M.Y. Park),노경호(K.H. Noh),박수형(S.H. Park),이재우(J.W. Lee),변영환(Y.H. Byun) 한국전산유체공학회 2008 한국전산유체공학회지 Vol.13 No.2
A supersonic viscous flow over a five-degree half-angle cone is studied computationally with three-dimensional Navier-Stokes equations. Steady asymmetric solutions show that the asymmetric flow separation is caused by convective instability. The effects of angle of attacks, Reynolds numbers, and Mach numbers have been investigated and it is found that those factors affect the generation of the side force. The side force has the maximum value at a=22°, while over a=22°, asymmetric vortex becomes transient, which results in the unsteady shedding. At the angle of attack of 22 degrees, the side force increases with Reynolds number and decreases with Mach number. The increase of the side force stops over the critical Reynolds number for the present configuration.
노경호(K.H. Noh),박미영(M.Y. Park),박수형(S.H. Park),이재우(J.W. Lee),변영환(Y.H. Byun) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
Computational Fluid Dynamics (CFD) and the Finite Element Method (FEM) are used to perform aerodynamics analysis and structure analysis. For the fluid-structure interaction analysis, each technology should be considered as well. The process of aerodynamics-structure coupled analysis can be applied to various integrated analyses from many research fields. In this study, the aerodynamics-structure coupled analysis is performed for the missile at high angle of attack condition through the use of Computational Fluid Dynamics (CFD) and the Finite Element Method (FEM). For this purpose, the aerodynamics-structure coupled analyses procedure for the missile are established. the results of the integrated analysis are compared with rigid geometry of the missile and the effect of the deformation will be addressed.