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RISS 인기검색어
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- 저자 : 이석준(S.J. Yee) (검색결과 6 건)
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로터 블레이드 제빙 시스템 설계를 위한 예측 코드 개발 및 결빙 풍동 시험
우철훈(C.H. Woo),김경삼(K.S. Kim),이석준(S.J. Yee),이재복(J.B. Yi),임태균(T.G. Lim),김정일(J.I. Kim),박남은(N.E. Park) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.11
When the helicopter is flighting through icing condition, the ice could be accreted on fuselage and blades. The ice on blade could deform the blade configuration and increase the weight of blade. The unstable motions of blade make decreasing of performance, handling quality and structural stability due to the abnormal weight increase and configuration change. The helicopter deicing system is required to avoid risk by icing. To protect the icing, the anti-icing system or the deicing system is used. Generally, the intake, the pitot sensor are adapted the anti-icing system, but the rotor blade uses deicing system because the large size heater mat of blade needs a lot of power consumption. The anti-icing system always actives heater mat in icing condition; the deicing system is run alternately by on/off time sequence to avoid ice accretion on blade. The design concepts of deicing system are needed estimation of heater mat location, scheduling on/off time sequence to avoid ice accretion, fixing of power consumption of heater mat. First of all, the icing region estimation on blade is needed to design of rotor blade deicing system. In this paper, air flow field and multi-phase fluid analysis was performed by the commercial CFD s/w, SC/Tetra to calculate the collection efficiency around objects. The ice accretion analysis was performed by developed in-house code, ASTROD based on Messinger thermodynamic model. The computation results show good estimation of ice accretion shape and ice thickness. The development of computational tool for icing/deicing is just one part of deicing system design process. The understanding of physical phenomenon of icing and deicing on blade surface is needed for design of deicing system. The icing/deicing wind tunnel test was performed to evaluate the function of deicing system of rotor blade that showed the phase changing on blade surface from ice to water at 0℃. And the deicing system design information was acquired from experimental results by on/off time scheduling.
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헬리콥터 로터 블레이드 제빙시스템 설계를 위한 블레이드 제빙해석 기법 연구
박남은(N.E. Park),우철훈(C.H. Woo),이석준(S.J. Yee),이재복(J.B. Yi),임태균(T.G. Lim) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
When the helicopter is flighting through icing condition, the ice could be accreted on fuselage and blades. The ice on blade could deform the blade configuration and increase the weight of blade. The unstable motions of blade make decreasing of performance, handling quality and structural stability due to the abnormal weight increase and configuration change. The helicopter deicing system is required to avoid risk by icing. Generally, the engine intake and the pitot sensor are adapted anti-icing system, but the rotor blade uses deicing system because the large size heater mat of blade needs a lot of power consumption. The anti-icing system is always active heater mat in icing condition; the deicing system is run alternately by on/off time sequence to avoid ice accretion on blade. Especially, due to the composite blade is weak by heat, over heat could make weak brittleness of blade. Thus, the de-icing system should be designed not only eliminate the ice on leading edge but also not damage the blade by heat source. First of all, the icing region estimation on blade is needed to design of rotor blade deicing system. In this paper, air flow field and multi-phase fluid analysis was performed by the commercial CFD s/w, SC/Tetra to calculate the collection efficiency around objects. The ice accretion analysis was performed by developed in-house code, ASTROD based on Messinger thermodynamic model. The computation result shows good estimations of icing region and ice thickness. In this study, de-icing situation is simplified that the blade surface adjoin with ice and thermal conduction occur at that interface. To analysis of convection on exterior surface of ice and internal heat power from heater mat by numerical method, discrete computational nodes of ice covered blade and consider phase change at the interface blade and ice. The numerical analysis result compared with ice wind tunnel test data of the blade to evaluate. The numerical method results show similar with experimental data about time to eliminate the ice and temperature of off-time range.
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박남은(N.E. Park),우철훈(C.H. Woo),이상기(S.G. Lee),이석준(S.J. Yee) 한국전산유체공학회 2008 한국전산유체공학회 학술대회논문집 Vol.2008 No.-
The development technology for the helicopter is improved by the increasing of computing power and advanced test facilities. The increasing efficiency of fuel consuming by the developing of improved lift-to-drag rotor system is the major issue, the noise reduction for ecology(civil area) and increase of survivability to reduce noise detection(battlefield) also are important. This investigation shows the classification of helicopter external noise and requirements, the noise flight test methods, the numerical modeling method for aero-acoustic of rotor blade and the result of CAA(Computational Aero-Acoustic) for main rotor blade.
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박남은(N.E. Park),우철훈(C.H. Woo),노현우(H.W. Rho),김철호(C.H. Kim),이석준(S.J. Yee) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
Helicopters and rotary-wing vehicles encounter a wide variety of complex aerodynamic phenomena and these phenomena present substantial challenges for computational fluid dynamics(CFD) models. This investigation presents the rotor aerodynamic analysis items for the helicopter development and variety aerodynamic analysis methods to provide the better solution to researchers and helicopter developers between aerodynamic problems and numerical aerodynamic analysis methods. The numerical methods to make an analysis of helicopter rotor are as below. - CFD Modelling: actuator disk model, BET model, fully rotor model, ... - Grid :sliding mesh, chimera mesh / structure mesh, unstructure mesh, ... - etc. : panel method, periodic boundary, quasi-steady simulation, incompressible, ... The choice of CFD methodology and the numerical resolution for the overall problem have been driven mostly by available computer speed and memory at any point in time. The combination of the knowledge of aerodynamic analysis items, available computing power and choice of CFD methods now allows the solution of a number of important rotorcraft aerodynamics design problems.
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전산공력소음해석을 통한 UH-60 제자리비행 공력소음 연구
박남은(N.E. Park),우철훈(C.H. Woo),최건묵(G.M. Choi),김철호(C.H Kim),이석준(S.J. Yee) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.4
The helicopter development technology is improved by the increasing of computing power and advanced test facilities. The increasing efficiency of fuel consuming by the developing of improved lift-to-drag rotor system is the major issue, the noise reduction for ecology(civil area) and increase of survivability to reduce noise detection(battlefield) also are important. This investigation shows the helicopter external noise flight test methods, conventional military helicopter's(UH-60) experimental results and the numerical modeling method for aero-acoustic of rotor blade and the result of CAA(Computalional Aero-Acoustic) for main rotor blade.
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