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고체산화물 전해질 직접탄소 연료전지의 전극 및 집전부 재질이 출력밀도에 미치는 영향
황준영(Hwang, J.Y.),윤재은(Yoon, J.E.),강경태(Kang, K.),김종훈(Kim, J.H.),이병준(Lee, B.J.) 한국신재생에너지학회 2009 한국신재생에너지학회 학술대회논문집 Vol.2009 No.06
Direct Carbon Fuel Cells (DCFCs) generates electricity directly converting the chemical energy in coal. In the present study, effects of anode and current collector materials on the power density of DCFC are investigated experimentally. The adopted DCFC system is combined type of solid oxide fuel cells (SOFC) and molten carbonate fuel cells (MCFC) with the use of a liquid-molten salt anode and a solid oxide electrolyte, proposed by SRI. Power densities of 25 mm button cells with various combination of anode materials and current collector materials are measured.
헬리콥터로부터 발사된 로켓의 공력 간섭 현상에 대한 수치적 연구
이범석(B.S. Lee),김유진(E.J. Kim),강경태(K.T. Kang),권오준(O.J. Kwon) 한국전산유체공학회 2011 한국전산유체공학회지 Vol.16 No.1
Numerical simulation of air-launched rockets from a helicopter was conducted to investigate the aerodynamic interference between air-launched rocket and helicopter. For this purpose, a three-dimensional inviscid flow solver has been developed based on unstructured meshes. An overset mesh technique was used to describe the relative motion between rocket and rocket launcher. The flow solver was coupled with six degree-of-freedom equation to predict the trajectory of free-flight rockets. For the validation, calculations were made for the impinging jet with inclined plate. The rotor downwash of helicopter was calculated and applied to simulation of air-launched rocket. It is shown that the rotor downwash has non-negligible effect on the air-launched rocket and its plume development.
헬리콥터로부터 발사된 로켓의 초기 안정성에 대한 수치적 연구
이범석(B. S. Lee),김유진(K. T. Kang),강경태(E. J. Kim),권오준(O. J. Kwon) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.11
Numerical simulation of air-launched rockets from a helicopter was conducted to investigate the initial aerodynamic stability and its plume effect. For this purpose, a three-dimensional inviscid flow solver has been developed based on unstructured meshes and an mesh technique was used to describe the relative motion between missile launcher and launched rockets. The flow solver was coupled with six degree-of-freedom equation to predict the trajectory of free-flight rockets. Simulation of air-launched rockets from a helicopter showed that rotor downwash has non-negligible effect on the initial stability of the rockets and its plume development.