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자장 방향 변화에 따른 밀폐공간 내 도전성 유체의 거동
한조영(C.Y. Han),전형열(H.Y. Jun),박응식(E.S. Park) 한국전산유체공학회 2009 한국전산유체공학회지 Vol.14 No.3
Hydromagnetic flow in a confined enclosure under a uniform magnetic field is studied numerically. The thermally active side walls of the enclosure are kept at hot and cold temperatures specified, while the top and bottom walls are insulated. The coupled momentum and energy equations associating with the electromagnetic retarding force as well as the buoyancy force terms are solved by an iterative procedure using the SIMPLER algorithm based on control volume approach. The changes in the .flow and thermal field based on the orientation of an external magnetic field, which varies from 0 to 2π radians, are investigated. Resulting heat transfer characteristics are examined too.
한조영(C.Y. Han),박응식(E.S. Park),전형열(H.Y. Jeon),유명종(M.J. Yu) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
Thermofluid flow analysis is major subject in most computational fluid dynamics applications. Accompanying convective and conductive heat transport phenomena, radiation plays an important role in high temperature operating systems. Cases in which the radiation dominates are found in such systems as boilers, furnaces, rocket engines, etc. In this paper the finite-volume method (FVM) are employed to simulate two-dimensional radiation problems in concentric and eccentric horizontal cylindrical annuli with general body-fitted coordinates. In thai case the simplest and intuitive remedies are proposed for mitigation of ray effect.
채종원(J.W. Chae),한조영(C.Y. Han) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
The authors have reviewed many mathematical thermal modelings of bipropellant propulsion system in literatures to gather basic data for developing a computer program which analyses the performance of bipropellant propulsion system. In this paper COMS and its propulsion system is briefly introduced for understanding. The set of first order nonlinear differential equations is reviewed and considered as candidate equations for the program development.
차세대 인공위성 전기저항제트 가스추력기의 다물리 수치모사
장세명(S.M. Chang),최진철(J.C. Choi),한조영(C.Y. Han),신구환(G.H. Shin) 한국전산유체공학회 2016 한국전산유체공학회지 Vol.21 No.2
NEXTSat-1 is the next-generation small-size artificial satellite system planed by the Satellite Technology Research Center(SatTReC) in Korea Advanced Institute of Science and Technology(KAIST). For the control of attitude and transition of the orbit, the system has adopted a RHM(Resisto-jet Head Module), which has a very simple geometry with a reasonable efficiency. An axisymmetric model is devised with two coil-resistance heaters using xenon(Xe) gas, and the minimum required specific impulse is 60 seconds under the thrust more than 30 milli-Newton. To design the module, seven basic parameters should be decided: the nozzle shape, the power distribution of heater, the pressure drop of filter, the diameter of nozzle throat, the slant length and the angle of nozzle, and the size of reservoir, etc. After quasi one-dimensional analysis, a theoretical value of specific impulse is calculated, and the optima of parameters are found out from the baseline with a series of multi-physical numerical simulations based on the compressible Navier-Stokes equations for gas and the heat conduction energy equation for solid. A commercial code, COMSOL Multiphysics is used for the computation with a FEM (finite element method) based numerical scheme. The final values of design parameters indicate 5.8% better performance than those of baseline design after the verification with all the tuned parameters. The present method should be effective to reduce the time cost of trial and error in the development of RHM, the thruster of NEXTSat-1.