• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.35-35
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• 1998

충격파의 경사반사는 초음속 비행체의 외부유동, 대형압축기의 디퓨져 내의 유동, 증기 터어빈 최종단 익렬유동, 데토네이션파가 벽면에 입사하는 유동 혹은 램제트의 연소공기 유입구 유동 등 초음속 유동에서 흔히 발생하며 이때의 유동장의 해석과 충격파 감쇄, 충격파와 간섭하는 벽면의 영향 등은 공학적으로 구명되어져야 할 중요한 문제이다. 전파하는 평면충격파가 벽면에 입사하는 경우 일어나는 충격파 경사반사는 크게 정상반사와 마하반사로 대별된다. 정상반사와 마하반사 간의 천이기준에 대한 연구는 오래 전부터 수행되어 왔고 입사충격파가 약한 경우 이론적 천이 기준인 이탈기준(detachment criterion)과 실험값의 차이 즉 Neumann paradox가 존재한다는 것이 밝혀졌다.

• Proceedings of the Korean Geotechical Society Conference
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• 1998.06a
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• pp.99-110
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• 1998

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.16-16
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• 1999

램 가속기 탄체 형상에 따른 가속 특성에 대한 연구는 열적 질식 모드에 대하여 Washington 대학, ISL 연구소 등에서 실험적으로 수행되어 졌으나 초폭굉 연소 모드에 대해서는 아직 미비한 실정이다. 초폭굉 연소 모드 램 가속기의 기본적인 탄체 형상은 원추-원통-원추로 이루어진 형상으로 탄체 전면에 형성된 경사 충격파가 탄체와 가속기 사이에서 반사되며 데토네이션파를 발생시켜 가속하게 된다. 탄체의 형상에 따라서 탄체 주위에 형성되는 충격파 구조는 차이를 나타내게 되고 발생되는 데토네이션파의 위치와 강도를 따라서 탄체의 가속특성은 상당한 차이를 나타낸다. 기본적으로 탄 체의 전면 형상은 경사 충격파의 강도와 단체 주위의 유동장의 특성을 결정하는 주요 요인이고 이에 따라 데토네이션파의 형성과 안정화 역시 결정되어 탄체의 가속 특성을 결정짓는다. 또한 데토네이션파를 임의의 위치에 형성하기 위해 이중 원추형상의 충격파-충격파 상호작용을 이용하여 데토네이션파를 발생시켜 탄체를 가속시킨다.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.5
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• pp.10-18
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• 2019

In this study, flow characteristics and the starting pressure of a center body diffuser (CBD) were analyzed at various center body (CB) positions and cone angles. According to the CB position, the location of oblique shock moved to the front from behind the CB cone with an increase in the flow momentum. Additionally, when a strong oblique shock occurred, the direction of supersonic flow was affected and induced to diffuser wall. As a function of different cone angles for the oblique shock, the starting pressure of the CBD was significantly affected.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.136-140
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• 2005

By extending one-dimensional ZND detonation structure analysis model, a simple model for two-dimensional oblique detonation wave structure analysis is presented by coupling Rankine-Hugoniot relation and chemical kinetics for oblique shock wave and oblique detonation wave. Base on this study, two-dimensional fluid dynamics analysis is carried out to investigate the detailed unsteady structure of oblique detonation waves involving triple point, transverse waves and cellular structures. CFD results provide a deeper insight into the detailed structure of oblique detonation waves, and the simple model could be used as a unified design tool for hypersonic propulsion systems employing oblique detonation wave as combustion mechanism.

• Journal of the Korean Crystal Growth and Crystal Technology
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• v.9 no.2
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• pp.240-244
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• 1999

Monolithic SiC and SiC/C functionally gradient material (FGM) layers were deposited on graphite substrates by CVD method. Temperature a profiles and thermal stress distributions in the deposited layers under the thermal shock were calculated by a commercially available software package. The designed FGM specimens were found to show an efficient relaxation of thermal stresses at the interfaces, and the specimens were intact even under a thermal shock of $\Delta$T=1600 K.

• Journal of the Korean Society for Marine Environment & Energy
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• v.10 no.4
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• pp.187-192
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• 2007

Impact on cylindrical surface caused by plunging breaking waves is investigated experimentally. The breaking waves are generated in a wave flume by decreasing the wave maker frequencies linearly and focusing the generated wave components at one specific location. The breaking wave packets are based on constant wave steepness spectrum. Three inclination angles of cylinder are applied to examine the effect of contact angle between cylinder and front surface of breaking waves. Also, the effect of cylinder diameter on pressure distribution and its peak value is investigated by adopting three cylinders with different diameters. The longitudinal location of cylinder is slightly moved in eight different points to find out a probable maximum value of impact pressure. The pressures and total force on cylinder surface are measured by piezo-electric pressure sensors and 3-components load cell with 30kHz sampling rate. The variation of peak impact pressures and forces is analyzed in terms of cylinder diameter, inclination angle and location. Also, the pressure distribution on cylindrical surface is examined. The cylinder location and surface position are more important parameters that govern the magnitude and shape of peak pressures, while the cylinder diameter and inclined angle are relatively insignificant. In a certain conditions, the impact phenomenon becomes very unstable which results in a large variation of measured valves in repeated runs.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.35 no.2
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• pp.33-40
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• 2023

Wave overtopping rate is one of the most important design parameters for coastal structures. In this study, the physical model tests for measuring the wave overtopping have been conducted with the foreshore slope in front of the seawall. The bottom seabed for the coastal road area was fabricated at the wave flume for two areas in the East sea areas. The wave overtopping rate was measured for various water depths and wave conditions in each coastal area. In particular, the impulsive wave conditions were compared with the previous research and the similar trends of wave overtopping was observed. It could be known that the effect of foreshore slope was significant and should be concerned for applying theses formula like EurOtop.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.14 no.2
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• pp.143-150
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• 2001

원자력발전소의 1차 계통에서 오염된 장비들을 취급이 용이하고 안전하게 운반하기 위한 운반용기는 내부의 방사성 물질에 대한 방사능 평가에 의하여 방사성물질 A형 운반용기로 분류된다. 방사성물질 A형 운반용기는 IAEA Safety Standard Series No. ST-1 및 국내 원자력법 등 관련규정의 기술기준을 만족하여야 하는데, 운반용기는 중량에 따라 0.3∼1.2m의 높이에서 소성이 일어나지 않는 단단한 바닥면으로 가장 심각한 손상을 주는 방향으로 낙하시키는 정상운반조건(normal transport conditions)에 대하여 구조적 건전성을 유지하여야 한다. 여기서는 ABAQUS/Explicit 코드를 이용하여 컨테이너형태의 A형 운반용기에 대하여 최대손상이 야기되는 0.9m 경사낙하조건에 대한 3차원 충격해석을 수행하고 구조적 건전성을 평가하였는데, 운반용기는 경사낙하시 코너피팅(corner fitting)의 분쇄(crush)에 의하여 대부분의 충격을 흡수하였으며 운반용기의 격납경계는 구조적 건전성을 유지하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.11
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• pp.914-921
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• 2017

The experimental research on a high-altitude environment simulation of space launch vehicle is important for securing independent technologies with launching space vehicles and completing missions. This study selected an altitude of 65 km for the experiment environment where it exceeded Mach number of 6 after the launch of Korean Space Launch Vehicle(KSLV-II). Shock tunnel was used to replicate the flight condition. After flow establishment, in order to confirm aerodynamic characteristics and normal and oblique shockwaves, the flow verification was carried out by measuring stagnation pressure and heat flux of a forebody model, and shockwave stand-off distance of a hemispherical model. In addition, a shock-free technique to recover free-stream condition has been developed and verified. From the results of the three verification tests, it was confirmed that the flow was replicated with the error of about ${\pm}3%$. The error between the slope angle of inclined shockwave of the scaled down transition section model using the shock-free shape and the slope angle of the horizontal plate model, and between the theoretical and the experimental value of the static pressure of the model were confirmed to be 2% and 1%, respectively. As a result, the efficiency of the shockwave cancellation technique has been verified.