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이재훈(J.H. Lee),이수강(S.G. Lee),이병주(B.J. Yi),이석희(S.H. Lee),이정헌(J.H. Lee),김희국(W.K. Kim) 한국정밀공학회 2004 한국정밀공학회 학술발표대회 논문집 Vol.2004 No.10월
In this study, a spatial 3-dof haptic mechanism is implemented. The implemented mechanism does not employ the gear transmissions as velocity reducers for all three joints but uses wire-based transmissions, thereby it is able to minimize the frictions significantly. Also, by employing the structure of the four-bar mechanism to drive third joint from close to the base, the mechanism is able to minimize the inertia effect from the third actuator very effectively. Its kinematic analysis such as position and velocity analyses are performed first. Then, its operating software development, hardware implementation, and the related interfaces between a PC and the implemented Haptic device are completed. To evaluate its potential and its performance as a haptic device, a experiment generating a virtual constraint in a operational task space is conducted and preliminary results are discussed.
이재훈(J. H Lee),김은기(E. G Kim),전기영(K. Y Jeon),전지용(J. Y Chun),이승환(S. H Lee),오봉환(B. H Oh),이훈구(H. G Lee),한경희(K. H Han) 전력전자학회 2007 전력전자학술대회 논문집 Vol.- No.-
In this paper, The authors design the current controller which independently control the d, q axis current transformed by the synchronously rotating d, q axis and a Space Vector Pulse Width Modulation(SVPWM) to steadily control the output DC-Link voltage against the variable load of the three phase PWM converter. Also, This study improves the high power factor, stability, and rapid response by the phase angle control using the digital Phase Locked Loop(PLL).
천이 SST 난류 모델을 이용한 3차원 날개 공력 해석
이재훈(J. H. Lee),정경진(K. J. Jung) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.11
In this study, aerodynamic coefficients are computed with the transition SST turbulence model for a three-dimensional wing. The transition SST turbulence model solves two additional transport equations to reflect the effect of the transition. Using this model, the three-dimensional wing of an aerial vehicle is solved, and their results are compared with other turbulence model. According to the numerical tests, the transition SST model predicts lower viscous drag which is resulted from the transition. Therefore, this model will be useful in the design of airfoils and wings in the transitional flow.
이재훈(J. Lee),권장혁(J.H. Kwon) 한국전산유체공학회 2008 한국전산유체공학회지 Vol.13 No.1
The fluid-structure interaction analysis such as a static aeroelastic analysis requires the result of each analysis as an input to the other analysis. Usually the grids for the fluid analysis and the structural analysis are different. so the results should be transformed properly for each other. The Infinite Plate Spline(IPS) and the Thin Plate Spline(TPS) are used in interpolating the displacement and the pressure. In this study, such interpolation methods are compared with kriging which provides a precise response surface. The static aeroelastic analysis is performed for the supersonic flow field with shock waves and the pressure field is interpolated by the TPS and kriging. The TPS shows tendency to weaken the shock strength, whereas kriging preserves the shock strength.
이재훈(J. Lee),정경진(K. Jung) 한국전산유체공학회 2016 한국전산유체공학회지 Vol.21 No.1
One of the obstacles on the grid generation for complex geometries with multi-block structured grids is the domain decomposition. In this paper, the domain decomposition for two-dimensional flow is studied using the flow characteristics. The potential flow equation with the source distribution on the panel surface is solved to extract the information of the flow. The current approach is applied to a two-dimensional cylinder and Bi-NACA0012 problems. The generated grids are applied to generic flow solvers and reasonable results are obtained. It can be concluded that the current methods is useful in the domain decomposition for the multi-block structured grid.