• Tunnel and Underground Space
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• v.11 no.3
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• pp.225-236
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• 2001

The roughness of rock joint is one of the most important parameters in developing the shear resistance and the tendency of dilation. Due to the damage accumulated with shearing displacement, the roughness angle is lowered continuously. It is known that dilation, shear strength hardening, and softening are directly related to the degradation of asperities. Much effort has been directed to incorporate the complicated damage mechanism of asperities into a constitutive model fur rock joints. This study presents an elasto-plastic formulation of joint behavior including elastic deformability, dilatancy and asperity surface damage. It is postulated that the plastic portion of incremental displacement 7an be decomposed into contributions from both sliding along the asperity surface and damage of asperity. Numerical cyclic shear tests are presented to illustrate th? performance of the derived incremental stress-displacement relation. A laboratory cyclic shear test is also simulated. Numerical examples reveal that the elasto-plastic joints model is promising.

• Journal of the Korean Geosynthetics Society
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• v.9 no.3
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• pp.39-45
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• 2010

When the ground temperature drops below $0^{\circ}C$, wet soils expand due to the ice formation in their porous space. This results in frost heave which causes structural stability problems. Frost heave is attributed by several factors such as physical soil properties and heat transfer including pore water phase change. Due to the complex physical phenomena, reliable and verified multi-dimensional numerical models for frost heave problems are still in a research stage. This study presents an efficient and simple method of overcoming numerical problems associated with sudden jump of heat capacity due to the phase change from water to ice in the pore space. This paper proposes heat transfer equation and finite element method when the saturated soils or porous rocks are subjected to freezing. Numerical analyses using the proposed method agree well with the known closed form solution and the laboratory test results.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.2
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• pp.1-7
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• 2002

In the modern propulsion systems, requited thrust is obtained using a nozzle. Sometimes shock and induced boundary layer separation is generated in an over-expanded convergent-divergent supersonic nozzle. It occurs because the nozzle expansion ratio is too large for a given nozzle pressure ratio (NPR). This phenomenon can be explained that it redefines effective nozzle geometry, shorer nozzle geometry and lower pressure ratio, in a given pressure ratio. Numerical studies were conducted about a fixed geometry 2D nozzle in overexpanded condition and compared with Hunter's experimental result. For the numerical simulation of the supersonic nozzle, Navier-Stokes equations are considered and as a turbulent model, $\kappa$-$\varepsilon$ /$\kappa$-$\omega$ blended SST two equation turbulent model is used. The characteristics of $\lambda$-shape shock systems due to the interaction of shock and boundary layer was investigated in a low NPR. And the result of comparison of thrust value shows that a fixed geometry nozzle can cover required flight mission.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.08a
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• pp.102-102
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• 2010

수 Tera Watt급의 가속기 및 펄스파워 시스템은 다수의 스위치를 사용하고 있으며, 이와 같은 가속기 및 시스템의 성능은 기체방전 스위치의 성능에 직접적으로 관련되어 있다. 일반적으로 이와 같은 기체방전, 액체방전 고출력 스위치는 다목적으로 많은 연구와 개발에 응용되고 있다. 예를 들어 천둥 펄스전자빔 발생장치는 12개의 Marx gap 및 3개의 100 kV 펄스충전 전기트리거 gap을 가지고 있다. 기체 방전 또는 액체 방전 펄스 충전 갭 스위치의 음극에 펄스 고전압이 인가되면 이로 인하여 음극에서 전자빔이 발생한다. 내부에는 전자빔이 양극과 충돌하는 순간 양극표면에 플라스마가 형성된다. 이와 같은 플라스마 sheath는 축 방향 이극관 안에서 양극충전 에서 음극으로 팽창하면서 전파하며, 또한 거의 동시에 음극표면에도 플라스마가 형성되어 음극에서 양극으로도 팽창하여 전파하게 된다. 이와 같은 펄스충전 고출력 갭 스위치 안에서 발생되는 방전 플라스마의 특성에 관한 갭 breakdown 과정에 대한 특성연구를 한다. 고출력스위치의 특성 조건으로는 방전전압, 방전시간, jitter 등이 있다. 본 연구에서는 최대전압 600 KV, 최대전류 88 KA, 펄스 폭 60 ns의 특성을 가지는 고전압펄스 시스템 '천둥'을 이용하여 방전 챔버에 고전압 펄스를 인가하고 N2와 SF6 혼합기체 종류와 압력에 따른 방전 현상을 연구하였다. 전극은 구리텅스텐 합금재질의 표준전극을 사용하였고, 전극 간격은 20 mm로 고정하였다. 방전 챔버 압력을 100 torr에서 4 기압까지 변화시켜가며 실험을 진행하였고, N2에 대한 SF6의 혼합비율을 0%~100%까지 변화시키며 실험을 진행하였다. 방전 챔버에는 C-dot probe와 B-dot probe를 설치하여 전압과 전류를 측정하였고, C-dot probe 와 B-dot probe는 각각 Northstar사의 10000:1 고전압 probe와 rogowiski coil을 이용하여 시준 하였다. 실험결과 방전전압은 압력이 증가함에 따라 증가하다가 2 기압 이상에서는 완만히 증가하는 경향을 보였고, SF6 혼합비율은 0~10%까지 급격히 증가하고, 그 이상의 혼합비율에서는 완만히 증가하였다. 방전개시시간은 혼합기체 압력에 따라 증가하며 1기압 이상에서는 급격히 증가 하였다. SF6 혼합비율에 따라서는 1 기압 조건까지는 큰 차이가 없었으나 2 기압부터는 급격히 증가하였다. 안정성을 나타내는 jitter는 SF6 100%일 때 가장 컸으나 혼합기체의 변화에 따른 큰 차이는 없었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.45-48
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• 2003

The plume interference is a complex phenomenon, consisting of plume-induced boundary layer separation, separated shear layer, multiple shock waves, and their interactions. The base knowledge of plume interference effect on powered missiles and flight vehicles is not yet adequate to get an overall insight of the flow physics in plume-freestream flow field. Computational studies are performed to better understand the flow physics of the plume-induced shock and separation for Simple, Rounded, Porous-extension test model configurations. The present study simulates highly underexpanded exhaust plume effect on missile body at the transoni $c^ersonic speeds. In order to investigate the plume-induced separation phenomenon, Simple, Rounded and Porous-extension plate are attacked to the missile afterbody. The computational result shows that the rounded afterbody and the porous-extension wall attached at the missile base can alleviate the plume-induced shock wave and separation phenomenon and improve the control of the missile body.dy.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.6
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• pp.38-44
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• 2010

The shock wave and boundary layer interaction patterns in an over-expanded rocket nozzle are associated with the production of undesirable side-forces during the start-up and shut-down processes of the engine. In the present work, a computational study is carried out to investigate the effect of the transient nozzle pressure ratio (NPR) on the flow fields inside the nozzle. The unsteady, compressible, axisymmetric, Navier-Stocks equations with SST k-${\omega}$ turbulence model are solved using a fully implicit finite volume scheme. NPR is varied from 2.0 to 10.0, in order to simulate the start-up and shut-down processes of the rocket engine. It is observed that the interaction patterns and the hysteresis phenomenon strongly depend on the time variation of NPR, leading to significantly different characteristics in the lateral forces.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.10
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• pp.809-815
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• 2014

The co-bonded dissimilar composite under a wide range of temperature change shows thermal distortion due to the differences in thermal expansion characteristics of the composite materials. Analysis of the thermal expansion characteristics of each composite is required for the design of co-bonded dissimilar composite structure with considering the shape distortion during the manufacturing process. In this work, digital image correlation (DIC) technique is introduced for measuring the thermal distortion characteristics of co-bonded dissimilar composite specimen, carbon/epoxy and silica/phenolic. The thermal distortion of co-bonded dissimilar composite specimen is numerically estimated and compared with the experiments. The estimated results is successfully validated using the measured results.

• Journal of the Korean Geotechnical Society
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• v.20 no.1
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• pp.5-12
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• 2004

The purpose of this paper is to make an understanding of fundamental mechanism of shear behaviour between rock and concrete interfaces in the pile socketed into granite. The interface of pile socketed in rock can be modeled in laboratory tests by resolving the axi-symmetric pile situation into the two dimensional situation under CNS(constant normal stiffness) direct shear condition. In this paper, the granite core samples were used to simulate the interface condition of piles socketed in granite in our country. The samples were prepared in the laboratory to simulate field condition, roughness(angle and height), stress boundary condition, and then tested by CNS direct shear tests. This paper describes shearing behaviour of socket piles into domestic granite through the analysis of CNS test results. It was found out that the peak shear strength increases with the angle of asperity and CNS value, and also the dilation increases with the angle of asperity but decreases with the CNS value.

• Proceedings of the Korean Vacuum Society Conference
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• 2015.08a
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• pp.168.1-168.1
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• 2015

자동차 산업분야에서 차량 경량화의 한 수단으로, 자동차용 유리를 무게가 가볍고 고강도 투명 고분자 소재인 폴리카보네이트로 대체하고자 하는 연구가 이루어지고 있다. 하지만, 폴리카보네이트의 낮은 내 마모 특성과 자외선에 의한 열화 및 변색 현상은 해결해야 할 문제점으로 지적되고 있다. 본 연구에서는, 폴리카보네이트의 내마모 특성을 향상시키기 위해 HIPIMS+ (High Power Impulse Magnetron Sputtering+) 방법을 이용하여 투과율이 확보되고, 고경도 특성을 갖는 Al-Si-N 박막을 증착하였다. 고속증착을 하기 위해 Target에 인가되는 Power를 올리게 되었는데, 열팽창 계수가 큰 고분자 물질인 폴리카보네이트 시료의 온도가 상승하여 증착된 박막과의 열팽창 계수 차이에 의해 박막에 Crack이 형성되는 문제가 발생하였다. 증착되는 Al-Si-N 박막의 공정 압력에 따른 Stress 제어 방법 및 폴리카보네이트 시료의 온도 상승을 막기 위한 알루미늄 구조체를 이용함으로써 박막의 Crack 형성을 억제하고자 하였다. 박막의 Stress를 확인하기 위하여 AFM (Atomic Force Microscope)과 OM (Optical Microscope)을 이용하여 분석하였고, 박막의 경도는 Knoop ${\mu}$-hardness tester를 사용하여 측정하였다. Al-Si-N 박막 경도는 Si at.%/(Al at.% + Si at.%) 비율이 16%에서 33 GPa의 경도를 갖는 것을 확인하였다. UV-Vis Spectrometer를 이용하여 투과율을 측정한 결과, 400-700 nm 파장의 가시광 영역 평균 투과율은 80%로 측정되었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.399-402
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• 2005

The present numerical study describes the flow physics on the interaction between the supersonic freestream and jet plume. The compressible flow past a simplified afterbody model with a sonic nozzle is investigated using mass-averaged Navier-Stokes equations, discretized by a fully implicit finite volume scheme, and the standard $k-{\omega}$ turbulence model. The results obtained through the present study are discussed specifically regarding the effect of the plume pressure ratio, freestream Mach number and base dimensions on the location of the plume-induced shock wave generated on the afterbody by the underexpansion of the jet plume.