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한국형 양심실 보조 인공 심장의 효율 분석 및 개선에 관한 연구
정진한,남경원,최성욱,이정주,박찬영,김욱은,최재순,민병구,Chung, J.H.,Nam, K.W.,Choi, S.W.,Lee, J.J.,Park, C.Y.,Kim, W.E.,Choi, J.S.,Min, B.G. 대한의용생체공학회 2001 의공학회지 Vol.22 No.5
한국형 양심실 보조 인공 심장의 효율 측정 방법과 측정 결과이다. 한국형 양심실 보조 인공 심장은 에너지 변환기로 브러시 없는 직류 모터를 사용한다 이 브러시 없는 직류 모터가 기어 열을 따라 원추운동을 하며 혈액주머니에 힘을 가하게 되고. 이 힘에 의해 혈액주머니 안의 혈액이 박출하게 된다. 효율 측정을 위하여 제어기 및 모터부, 기어부 및 작동기부. 혈액주머니 및 기타부 등 크게 세 부분으로 나누었으며. 각각을 다시 소자별로 나누어 입. 출력의 효율을 측정했다. 부하의 토크, 분당 회전수 각속도, 인가되는 전압 등을 바꾸어 가면서 시스템의 효율을 측정했고. 이 측정을 통해서 모터 운동시의 전체적인 효율과 부분별 효율을 알 수 있었다. 특히 양심실 보조 장치의 모터부와 작동기부의 효율측정에 중점을 두었다. 측정 결과 이동 작동기형 양심실 보조 장치의 평균 동작 영역인 4$\ell/min$ 박출량에서, 전체 효율은 8 %정도이며 구체적으로는 모터부 50 %, 작동기부 85 % 혈액주머니부 19 %정도의 효율을 보였다. 또한 6$\ell/min$ 박출량의 경우, 전체 효율은 5.5 %정도였다. 분석된 결과를 바탕으로 효율을 개선하기 위해 박출량에 따른 필요 구동 전압을 결정하고. 혈액주머니의 충만 상태에 따른 속도 파형을 연구. 제안하였다. This is a test report of system efficiency for the moving-actuator type Bi-ventricular assist device (AnyHear $t^{MT}$ ) Seoul National University). $AnyHeart^{TM}$), as an energy converter. utilities a brushless DC motor(S/M 566-26A. Sierracin/ Magnedyne, Carlsbad, CA. U.S.A.) generating their pendulous motion in the epicyclic gear train. It is necessary to know about the overall efficiency of the system. The system is subdivided into three parts: motor part, actuator part and blood sac part (including valves, etc.) according to system mechanism. The motor was operated with a variable range of torque. angular speed and width of voltage Pulse In this report. $AnyHeart^{TM}$ is focused on the efficiency of the motor and actuator parts. 4 $\ell/min$ pump output. which is normal condition of $AnyHeart^{TM}$ system, the total system efficiency is 8%, which is composed of 50%, 85% and 17% efficiency (motor Part, actuator Part and blood sac Part) respectively. In the analyzed result. applied input voltage on normal condition of $AnyHeart^{TM}$ is determined. Also speed Profile with considering filling state of blood sac is Provided. In the test of the in vitro mock circulation. some experimental results are Provided to demonstrate the effectiveness of the Presented approach.
보존적 중첩격자기법을 이용한 동적 플랩의 천이적 공력거동에 관한 수치적 연구
최성욱(S. W. Choi),장근식(K. S. Chang),김인선(I. S. Kim) 한국전산유체공학회 2000 한국전산유체공학회지 Vol.5 No.2
Transient aerodynamic response of an airfoil to a moving plane-flap is numerically investigated using the two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a 'Dynamic Domain Dividing Line' which has an advantage for constructing a well-defined hole-cutting boundary. A conservative Chimera grid method with the dynamic domain-dividing line technique is applied and validated by solving the flowfield around a circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver are also examined by computations of an oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number.
최성욱(S.W. Choi),김인선(I.S. Kim) 한국전산유체공학회 2001 한국전산유체공학회 학술대회논문집 Vol.2001 No.-
Flow computations have been conducted to study the impingement flow field over the KSR-Ⅲ flume deflector. To validate Euler solver for the jet impingement flowfield, the jet flow over a double wedge deflector have been calculated and showed reasonable agreement with experimental data. The transient flow behavior of flume over deflector have been investigated and the flume from the rocket nozzle proved to he getting out of the deflector safely and the thermal effect on the base region of rocket was not considerable.
보존적 중첩격자기법을 이용한 동적 플랩의 천이적 공력거동에 관한 수치적 연구
최성욱(S. W. Choi),장근식(K. S. Chang) 한국전산유체공학회 1999 한국전산유체공학회 학술대회논문집 Vol.1999 No.-
Transient aerodynamic response of an airfoil to a moving plane. flap is numerically investigated using two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a' dynamic domain, dividing line' the concept of which is developed in this study. A conservative Chimera grid method with a dynamic domain-dividing line technique is applied and validated by solving the flowfield around circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver is also examined by computations of a oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number.
최성욱(S.W. Choi),김재무(J.M. Kim) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
Unsteady flow simulation for the tiltrotor Smart UAV configuration was performed to investigate the powered rotor wake effect on aerodynamic characteristics. Calculations were performed to simulate various flow conditions based on different flight modes including hover, conversion and cruise. Three-dimensional compressible Navier-Stokes equation code were used for flow calculation and Chimera grid technique overlapping individually generated grids was employed A dynamic grid method was adopted in simulation of the rotating blades. Flow calculations were also conducted for the un-powered case. Aerodynamic interaction between the rotor and airframe was investigated comparing three data sets from the un-powered, powered, and isolated rotor cases.
최성욱(S. W. Choi),장근식(K. S. Chang) 한국전산유체공학회 2000 한국전산유체공학회 학술대회논문집 Vol.2000 No.5
Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated using a two-dimensional turbulent compressible Navier-Stokes flow model. The spoiler moving relative to a stationary airfoil is treated by an overset grid bounded by a 'dynamic domain-dividing line' the concept of which is developed first in this paper. The fluid-dynamic mechanism of the adverse lift due to the rapidly deploying spoiler is analyzed. Also the effect of spoiler deploying rate on the initial behavior of the aerodynamic response is expounded, which is of interest in view of active control technology and controller design for the spoiler. The results of present computation about the stationary as well as moving spoilers are relatively in good agreement with the existing experimental data.