• Proceedings of the Korean Society of Precision Engineering Conference
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• 1993.04b
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• pp.18-22
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• 1993

본 논문은 H-형상 단면의 측대칭 부품에대하여 컴퓨터에 의한 열간단조 공정설계 및 금형설계 시스템을 개발하고 슬래브 해석법을 이용한 단조 시뮬레이션 프로그램을 통하여 단조하중을 예측하고자 한다. 이 시 스템을 수행하기 위한 컴퓨터 프로그램의 입력사항은 축대칭 H-형상 단조품 단면의 기하학적 형상, 소재비 도는 단조비, 마찰조건, 램속도, 다조온도, 소재 및 다이 재료명 등이다. 시스템의 실행 후 얻은 결과들은 실제 산업 현장의 요구에 맞추어 빌렛 형상, 예비 성형체, 그리고 최종다이 및 예비성형 다이가 도면화 되 어 출력된다. 수행된 출력결과가 사용자의 요구와 일치하지 않을 경우 입력사항을 변경하여 재 설계할 수 있도록 되어 있다. 그리고 본 시스템은 크게 세개의 모듈 즉, 공정설계 모듈, 시뮬레이션 모듈 등으로 구성되어 있고 각각의 모듈은 독립적으로 또는 통합하여 수행된다.

• Journal of the Korean Society of Visualization
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• v.12 no.3
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• pp.21-25
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• 2014

Optical distortion of experimental results can be found in many studies. Thus, a method of the optical correction for visualization of an axisymmetric droplet was developed in this study. The correction method was derived to extract refracted vectors. In order to obtain the refracted vectors, a projection vector and a normal vector should be calculated. Then, a distortion distance can be found by the calculated refracted vector and Snell's law. The developed method was also verified by the simulation and the experimental results to apply for a liquid droplet which was formed at a nozzle tip.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1994.10a
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• pp.295-299
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• 1994

두꺼운 원통형 쉘은 공학적인 문제에서 많이 사용된다. 쉘 내부에 임피던스가 큰 유체와 구조물이 있을 때 쉘을 포함한 진동해석은 이론적인 해석이 매우 어렵다. 쉘 내부에 있는 유체의 임피던스가 공기에 비하여 매우 클 경우 쉘과 유체, 내부의 구조물과 유체사이의 구조물-유체 상호작용(structure-fluid interaction)이 고려되어야 한다. 얇은 원통형 쉘에 대해서는 상용 유한요소 코드를 이용하여 구조물-유체 상호작용을 고려한 진동해석이 많이 수행되었으나 축대칭 두꺼운 원통형 쉘에 대해서는 연구가 수행되지 않고 있다. 본 연구에서는 NASTRAN, ANSYS 같은 상용 유한요소 코드에서 지원되지 않는 축대칭 두꺼운 원통형 쉘 내부에 유체와 강체요소가 있을 경우 이에 대한 유한요소 코드를 개발하고, 구조물-유체 상호작용을 고려하여 진동해석을 하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.81-86
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• 2004

Between rolling airframe missile and swirling propulsion jet passing through convergent-divergent nozzle of the rocket motor, occur exchanges of angular momentum which result in the increase of roll speed of the missile. This phenomena in called jet roll damping. In the study jet roll damping was formulated from conservation equation of angular momentum. And the maximum value of the jet roll damping of KPSAM was estimated with assumed swirl velocity distribution at nozzle exit and compared with result of computation of axisymmetric compressible turbulent nozzle flow.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.450-454
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• 2005

A numerical analysis is performed to analyze the reacting flow-field of an axisymetric coaxial ramjet combustor. Two dimensional Navier-Stokes equation with low Reynolds number $k-\varepsilon$ turbulence model is utilized and finite-rate chemistry model is adopted. Eddy dissipation model is applied for a modeling of turbulent combustion. Two different types of combustors (combustor with a suddenly expanded dump and combustor with wedge-shaped flame holders) are compared in a view point of flame stabilizing.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.565-569
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• 2011

A two-dimensional thermal response and ablation analysis code for predicting charring material ablation and shape change on solid rocket nozzle is presented. For closing the problem of thermo-structural analysis, Arrhenius' equation and Zvyagin's ablation model are used. The moving boundary problem are solved by remeshing-rezoning method. For simulation of complicated thermal protection systems, this method is integrated with a three-dimensional finite-element thermal and structure analysis code.

• Solar Energy
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• v.10 no.1
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• pp.31-37
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• 1990

An experimental study for the flow in an axisymmetric cavity of rectangular tube was performed. The pressure and heat transfer coefficient along the side and opposite-walls of the cavity were measured. The cavity length was varied from 80mm to infinity during the experiment. As the result of this study, it was found that as the length of cavity increased beyond the reattachment point, the heat transfer coefficient decreased. It was also found that the mean heat transfer coefficient became maximum near the reattachment point.

• Journal of computational fluids engineering
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• v.2 no.2
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• pp.35-43
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• 1997

An efficient inverse method for 1.he supersonic/hypersonic axisymmetric body design is developed for the parabolized Navier-Stokes equations. The developed method is examined numerically for three extreme testcases in the supersonic(M/sub ∞/=3.0) and hypersonic(M/sub ∞/=6.28) speeds. The first one is a negative pressure distribution near a vacuum pressure and the second one is a positive pressure distribution over the whole region of the body. The last one is the case of abrupt change of pressure distribution to zero in the forward region of the body. These testcases show the robustness of the method. By introducing a regular-falsi method and by using a not-fully converged inverse solution, the convergence behavior was greatly improved.

• 한국전산유체공학회:학술대회논문집
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• 2007.10a
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• pp.39-44
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• 2007

A similarity solution of the Navier-Stokes equation for the axisymmetric stagnation flow near a plane wall coated with a magnetic fluid of uniform thickness is constructed. The shape functions representing the flow in two (magnetic and normal) fluid layer are determined from a third order boundary value problem, which is solved by the Runge-Kutta method with two shooting parameters. Features of the flow including streamline pattern and interface velocity are investigated for the varying values of density ratio, viscosity ratio, and Reynolds number. The results for the interface and wall shear stress, boundary layer and displacement thickness are also presented.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.6
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• pp.1070-1081
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• 1989

본 논문의 목적은 일반적인 곡면을 갖는 냉간단조 공정을 컴퓨터 시뮬레이션 을 통해 해석하고자 강소성 유한요소법의 프로그램을 개발하고, 이를 축대칭 및 평면 변형 단조성형에 적용하고자 한다. 축대칭 문제로는 산업적으로 이용이 많은 치차 블랭크(gear blank) 형태의 예제를 선택하였고 평면변형으 경우 정밀 단조품의 하나인 터어빈 블레이드(turbine blade)를 평면변형 문제로 보아 해석하였다. 한편 심한 변형을 하는 후방압출과 같은 문제의 수렴성을 향상시키고 공정을 계속적으로 해석하 기 위하여 격자 재구성기법을 도입함으로서 냉간단조 문제의 일반적인 해석을 하도록 한다.