• 항공우주시스템공학회지
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• 제17권4호
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• pp.43-57
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• 2023

우주 물체 및 우주 구조물의 초고속 충돌 시뮬레이션을 LS-DYNA를 사용하여 수행하였다. 구형, 원뿔형, 및 속이 빈 원통형의 다양한 형상의 우주 물체는 SPH(Smoothed Particle Hydrodynamics)를 사용하여 모델링하였다. 다양한 두께의 우주 구조물은 직접 충돌 영역과 간접 충돌 영역으로 나누어, 각각 SPH 및 유한 요소를 사용하여 나타내었다. 초고속 충돌에서 금속 재료의 비선형 거동을 나타내기 위하여 Johnson-cook 재료 모델과 Mie-Grüneisen 상태 방정식을 사용하였다. 우주 물체의 형상, 우주 구조물의 두께, 충돌 각도, 및 충돌 속도의 다양한 충돌 조건을 고려하였다. 파편운은 우주 물체와 우주 구조의 초고속 충돌로 인해 발생되며, 발생된 파편운의 형상을 정량적으로 분석하였다. 본 연구의 모든 충돌 조건에서, 원뿔 형상의 우주 물체로 인한 파편운이 가장 위험한 형상임을 확인하였다.

• 대한기계학회논문집
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• 제8권1호
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• pp.57-64
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• 1984

Forward extrusion of sintered porous metal through conical converging die is analyzed using slab method on the basis of plasticity theory for porous metal. It is taken into consideration in the analysis that the material in the container is continuously recompressed on densified until the process reaches steady state. Extrusion pressure and distribution of relative density from the die inlet to the outlet are calculated under various process variables. The results are useful in finding initial relative density of the billet, reduction of area and cone angle of the die in order to get required final products. Experiments are done for porous copper and then compared with the computed results.

• 대한기계학회논문집
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• 제7권2호
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• pp.168-174
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• 1983

The study is concerned with an analysis on the hydrofilm extrusion through conical dies. The upper bound method is adopted for the analysis of metal deformation in connection with hydrodynamic lubrication theory for the lubricant in order to determine the extrusion pressure for some variables such as reduction of area, die cone angle. In the upper bound method, a kinematically admissible velocity field is found by assuming proper streamlines and applying the flow function concept to the region of plastic deformation. The effect of work hardening is incorporated approximately by calculating the strains at the exit of the die. The experiments are carried out with the commercially pure aluminium for some chosen variables at room temperature. It is shown that the theoretical predictions are in good agreement with the experimental observations.

• 한국소성가공학회:학술대회논문집
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• 한국소성가공학회 2002년도 금형가공 심포지엄
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• pp.225-230
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• 2002

As in most metal forming processes, die and lubrication are of vital importance in hydrostatic extrusion. An efficient die design and lubrication system selection reduce the pressure required for a given reduction ratio by lowering friction at the billet-die interface. In contrast to the conventional macroscopic extrusion, fine-wire fabrication requires higher extrusion pressure and effect of friction is much more significant. Forming fine Au, Ag, and Cu wire with hydrostatic extrusion process in cold condition, the effect of extrusion die angle, lubrication and billet's initial diameter was studied.

• 한국정밀공학회지
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• 제11권2호
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• pp.110-119
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• 1994

The Robust Controller for scan-loop is designed using LQG/LTR Methodology. The design and analysis of spiral, rosette and conical scan patterns are discussed. The perfermance and robustness of the LQG/LTR controller are analyzed through experiments and cpmpared with those of the P-controller. Especially to improve the scan performance at large look angle, the cage coil output is linearized using a binomial equation. It is demonstrated that the scan-loop system by the LQG/LTR control is very robust to phase uncertainties.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.32-33
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• 2003

Mechanism of a periodic oscillation of shock-induced combustion over a two- dimensional wedges and axi-symmetric cones were investigated through a series of numerical simulations at off-attaching condition of oblique detonation waves(ODW). A same computational domain over 40 degree half-angle was considered for two-dimensional and axi-symmetric shock-induced combustion phenomena. For two-dimensional shock-induced combustion, a 2H2+02+17N2 mixture was considered at Mach number was 5.85with initial temperature 292 K and initial pressureof 12 KPa. The Rankine-Hugoniot relation has solution of attached waves at this condition. For axi-symmetric shock-induced combustion, a H2+2O2+2Ar mixture was considered at Mach number was 5.0 with initial temperature 288 K and initial pressure of 200 mmHg. The flow conditions were based on the conditions of similar experiments and numerical studies.[1, 3]Numerical simulation was carried out with a compressible fluid dynamics code with a detailed hydrogen-oxygen combustion mechanism.[4, 5] A series of calculations were carried out by changing the fluid dynamic time scale. The length wedge is varied as a simplest way of changing the fluid dynamic time scale. Result reveals that there is a chemical kinetic limit of the detached overdriven detonation wave, in addition to the theoretical limit predicted by Rankine-Hugoniot theory with equilibrium chemistry. At the off-attaching condition of ODW the shock and reaction waves still attach at a wedge as a periodically oscillating oblique shock-induced combustion, if the Rankine-Hugoniot limit of detachment isbut the chemical kinetic limit is not.Mechanism of the periodic oscillation is considered as interactions between shock and reaction waves coupled with chemical kinetic effects. There were various regimes of the periodicmotion depending on the fluid dynamic time scales. The difference between the two-dimensional and axi-symmetric simulations were distinct because the flow path is parallel and uniform behind the oblique shock waves, but is not behind the conical shock waves. The shock-induced combustion behind the conical shockwaves showed much more violent and irregular characteristics.From the investigation of characteristic chemical time, condition of the periodic instability is identified as follows; at the detaching condition of Rankine-Hugoniot theory, (1) flow residence time is smaller than the chemical characteristic time, behind the detached shock wave with heat addition, (2) flow residence time should be greater than the chemical characteristic time, behind an oblique shock wave without heat addition.

• 한국항공우주학회지
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• 제47권3호
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• pp.195-203
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• 2019

극초음속 영역에서 운용되는 스크램제트엔진의 흡입구는 엔진 전체 성능에 직접적으로 연관되어 있으므로 개발에 앞서, 다양한 조건에서의 성능 특성 분석이 필수적이다. 본 연구에서는 축대칭 내부 압축형 흡입구인 Busemann과 외부 압축형 흡입구 형상을 설계하고, 설계점 및 탈설계점에서의 전산해석을 수행하였다. 해석결과를 토대로, 마하수와 받음각에 대한 극초음속 흡입구의 전반적인 성능 특성을 파악하였다. Busemann 흡입구는 $2^{\circ}$의 Truncation 각에 따라 흡입구의 길이를 단축하여도 성능 저하가 미미하였으며 탈설계 마하수에서는 흡입구 성능이 우수하였으나, 받음각이 있는 경우 시동 특성이 크게 저하되었다.

• 구강회복응용과학지
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• 제30권3호
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• pp.206-214
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• 2014

목적: 내부 원추형 연결형태 임플란트에서 지대주 나사의 좌면각도가 연결부의 기계적 안정성에 미치는 영향을 알아보기 위함이다. 연구 재료 및 방법: 원추형 연결구조 티타늄 임플란트와 시멘트 유지형 지대주, 텅스텐 카바이드 코팅된 티타늄 합금 지대주 나사를 사용하였다. 좌면각도가 $45^{\circ}$와 $90^{\circ}$를 갖는 지대주와 지대주 나사를 제작하여 30 Ncm 조임회전력으로 지대주를 체결한 후 하중을 가하고 체결 및 하중 부여에 따른 침하량을 측정하였다(n = 5). 유압식 피로시험기에 임플란트를 고정하고 스테인리스 스틸 금속관을 지대주에 합착하였다. 이 후 반복 하중을 가한 후 풀림토크 변화량을 측정하고, 압축굽힘강도와 피로강도를 측정하였다(n = 5). 결과: 지대주 침하량은 지대주나사 체결 시 가장 크게 나타났으며(P < 0.05), 나사체결과 하중부여에 따른 총 침하량은 $45^{\circ}$군보다 $90^{\circ}$군에서 더 크게 측정되었다(P < 0.05). 반복하중 부여 후 풀림 토크, 그리고 최대 압축굽힘강도와 피로강도는 통계적으로 유의한 차이를 보이지 않았다(P > 0.05). 결론: 본 실험조건하에서 지대주 나사머리의 원추형 설계가 지대주의 총 침하량을 약간 감소시키는 효과를 나타냈으나, 연결부의 전체적인 기계적 안정성에 미치는 영향은 크지 않을 것으로 판단된다.

• 대한조선학회논문집
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• 제55권3호
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• pp.252-264
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• 2018

The calculation of steady-state cavitating flows around Supercavitating Underwater Bodies (SUB's), which consist of a circular disk head (cavitator), a conical fore-body, a cylindrical middle-body and either a boat-tail or a flare-tail, are carried out. To calculate the axisymmetric cavitating flow, used is a commercial computational fluid dynamics code based on the finite volume method, Fluent. From the analysis of numerical results, the cavity and drag, affected by the fore-body and tail of the SUB's, are investigated. Firstly, the effect of the fore-body shape is investigated with the same disk cavitator and a cylindrical rear-body of fixed diameter. Then with the same cavitator and a fixed fore-body, the effect of the rear-body shape is investigated. Before the cavity generated by the cavitator covers the slant of fore-bodies sufficiently, the larger the cone angle of the fore-body(i.e., the shorter the slant length), the larger the drag and the slower the development of cavity. After the cavity covers the fore-body completely so that the pressure drag component of the body is vanished, the characteristics of drag-velocity curves are identical. Also, as the tail angle is bigger, the cavity generated by the cavitator is suppressed further and the drag becomes larger. The peak of the drag appears for the flare-tail, i.e., when the tail angle is positive(+). On the contrary, the trough of the drag appears for the boat-tail, i.e., when the tail angle is negative(-). When the tail angle is 5 degrees, the peak of the drag appears at the body speed of 80m/s and the value of the drag is 43% larger than that at the design speed of 100m/s. When the tail angle is -5 degrees, the trough of the total drag appears at 75m/s and that drag is 30% smaller than that of the cavitator, which means the rest of the body has a negative drag.

• 지질공학
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• 제6권2호
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• pp.53-58
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• 1996

암석 시료의 파괴시에 발생하는 AE신호를 측정하여 파괴와 관련된 미세균열의 발생원에 대한 연구를 위하여서는 탐촉자에서 기록장치까지 전과정에 대한 검증이 필요하다. 특히 탐촉자는 기계적인 진동을 전기신호로 전환하는 기능을 가진 예민한 장치로서 다양한 인자에 의하여 예민도가 달라질 수 있기 때문에 보정시험을 실리하여야 한다. 압전 압력형 PAC 탐촉자를 NBS나 DG의 변위형 탐촉자에 의하여 보정하는 시험을 실시하였다. NBS 및 PAC탐촉자는 파의 입사방위각에는 무관하나 입사각에는 예민하게 반응한다. 즉, 입사각이 $90^{\circ}$ 일 때에는 입사각 $15^{\circ}$ 이하 일 때보다 약 10배의 큰 출력을 나타내었다. 또한, 시험에 사용된 PAC 탐촉자가의 경우 강도에 대한 개별 예민도의 차이가 최대 약 40%이었다. 압력형 PAC 탐촉자는 변위형 표준탐촉자로 절대치 보정시험을 실시한 결과 보정계수는 평균 77mv/pm이었다.