• 한국전자파학회논문지
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• 제19권6호
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• pp.698-705
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• 2008

전자파가 대기를 통과할 때 대기를 형성하고 있는 다양한 요인들에 의해 그 특성이 변동하게 된다. 전파 특성에 영향을 미치는 대기의 주요 요인으로는 수증기, 안개, 산소와 같은 대기 입자, 강우, 강설 및 그 외 여러 종류의 에어로졸을 들 수 있으며, 이러한 것들은 지형 및 지역적 특성에 따라 다르게 분포한다. 따라서 대기 환경에서의 전파 특성을 예측하기 위해서는 주어진 환경에 대한 기온, 습도, 기압, 풍속, 에어로졸 및 강우율 등의 통계적 분석이 중요하다. 본 논문에서는 국내 대기 환경에 대한 통계적 분석을 수행하였으며, 이를 바탕으로 국내 대기 환경에서의 전파 특성을 분석하였다.

• 한국음향학회:학술대회논문집
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• 한국음향학회 1999년도 학술발표대회 논문집 제18권 2호
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• pp.427-432
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• 1999

When a high-speed train enters a tunnel, a compression wave is generated. This wave subsequently emerges from the exit portal of the tunnel, which causes an impulsive noise called 'Sonic boom' or 'micro-pressure wave'. In the present study, new method is presented for prediction of sonic boom noise, especially focusing on the effect of the nose shape of the train on the resultant noise. Acoustic theory for monopole source is used to represent a nose shape of the train in wave equation. Compression wave propagation in tunnel considering tunnel track condition and emission of sonic boom was calculated. The predicted compression waves and impulsive sound waves are compared with recent measurements, and show reasonable agreements.

• 한국항공우주학회지
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• 제47권8호
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• pp.599-606
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• 2019

펄스건 장치는 연소실 내, 다중 분사기 배열에 따른 연소 유동장으로의 횡단 압력파 전파/감쇠 메커니즘 규명을 목적으로 제작되었다. 제작된 펄스건은 성능시험을 통해 목표 연소압에서의 운용 가능 여부와 압력파 강도 제어 여부를 확인하였다. 기체질소를 사용하여 고압관에 가압을 하였으며 다이아프램에는 $100{\mu}m$ 두께의 OHP 필름을 사용하였다. 압력파의 속도와 강도를 확인하기 위해 압력 트랜스듀서를 이용하여 동압과 정압을 측정하였다. 제작된 펄스건은 공급압력에 따라 압력파의 강도 조절이 가능하며 횡방향성을 가지는 압력파를 생성할 수 있음을 성능시험을 통해 확인하였다.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2003년도 유체기계 연구개발 발표회 논문집
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• pp.671-677
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• 2003

Two-dimensional direct numerical simulation of the edge-tones by the finite difference lattice Boltzmann method (FDLBM) is presented. We use a new lattice BGK compressible fluid model that has an additional term and allow larger time increment comparing the conventional FDLBM, and also use a boundary fitted coordinates. We have succeeded in capturing very small pressure fluctuations result from periodically oscillation of jet around the edge. That pressure fluctuations propagate with the sound speed. It is clarified that the sound wave generated in rather wide region and individual vortices do not affect the sound wave propagation.

• 대한조선학회논문집
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• 제54권5호
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• pp.439-446
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• 2017

This paper deals with an experimental study of the dynamics of an underwater bubbles and shock waves, generated by rapid underwater release of highly compressed gas. Aribag inflators, which are used for automobile's airbag system, are used to generate the extremely-rapid underwater gas release. Experimental studies of the complex underwater bubble dynamics as well as underwater shock wave were carried out in a specifically designed cylindrical water tank. The water tank is equipped with a high-speed camera and pressure sensors. The high-speed camera was used to capture the expansion and collapse of the gas bubble created by inflators, while pressure sensors was used to measure the underwater shock propagation and magnitudes. The experimental results were compared against the results of explosion of pentolite explosive. Several physical phenomena that has been observed and discussed, which are different from the explosive underwater explosion.

• 대한환경공학회지
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• 제27권10호
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• pp.1065-1071
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• 2005

유체의 파속과 파형을 이용한 많은 누수탐지 기술들이 연구되고 있다. 본 연구에서는 파속을 계산하기 위해 천이류 방법을 이용하였고 누수지점의 탐지를 위해 주파수 분석방법을 개발하였다. 가압관망의 자료획득 시스템을 개발하였으며, 이를 통해 고주파 수압자료를 획득하였다. 이들 방법론은 측정과 모의 과정에서 발생되는 오차로 인한 불화실성을 적절히 처리할 수 있으며, 수압자료의 측정간을 근거로 누수의 예측지점을 추정할 수 있다. 본 연구에서 개발된 방법은 수압자료로부터 확보되는 정보를 기반으로, 누수가 동반된 천이현상에서 누수예측능력을 보여주고 있다.

• 한국추진공학회지
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• 제16권3호
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• pp.16-23
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• 2012

정상초음파의 교반이 메탄/공기 예혼합화염의 동역학적 거동에 미치는 영향을 규명하는 실험 결과를 본 연구에서 제시한다. 슐리렌 기법을 이용하여 전파하는 화염을 가시화하였고, 이미지 후처리를 통해 정상초음파 유무에 따른 화염선단의 전파속도를 상세히 관찰하였다. 전파속도는 이론당량비에서 정상 초음파가 교반하는 경우에 크게 증가하였으며, 당량비가 연소 상한계 혹은 연소 하한계로 벗어남에 따라 교반의 효과는 감소하였다. 정상초음파장은 화염 구조의 왜곡을 동반하고, 그 변이 형상은 교반하는 초음파장의 특성에 전적으로 종속하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 학술대회
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• pp.367-373
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• 2008

Spinning detonations propagating in a circular tube were numerically investigated with a one-step irreversible reaction model governed by Arrhenius kinetics. Activation energy is used as parameter as 10, 20, 27 and 35, and the specific heat ratio and the heat release are fixed as 1.2 and 50. The time evolution of the simulation results was utilized to reveal the propagation mechanism of single-headed spinning detonation. The track angle of soot record on the tube wall was numerically reproduced with various levels of activation energy, and the simulated unique angle was the same as that of the previous reports. The maximum pressure histories of the shock front on the tube wall showed stable pitch at Ea=10, periodical unstable pitch at Ea=20 and 27 and unstable pitch consisting of stable, periodical unstable and weak modes at Ea=35, respectively. In the weak mode, there is no Mach leg on the shock front, where the pressure level is much lower than the other modes. The shock front shapes and the pressure profiles on the tube wall clarified the mechanisms of these stable and unstable modes. In the stable pitch at Ea=10, the maximum pressure history on the tube wall remained nearly constant, and the steady single Mach leg on the shock front rotated at a constant speed. The high and low frequency pressure oscillations appeared in the periodical unstable pitch at Ea=20 and 27 of the maximum pressure history. The high frequency was one cycle of a self-induced oscillation by generation and decay in complex Mach interaction due to the variation in intensity of the transverse wave behind the shock front. Eventually, sequential high frequency oscillations formed the low frequency behavior because the frequency behavior was not always the same for each cycle. In unstable pitch at Ea=35, there are stable, periodical unstable and weak modes in one cycle of the low frequency oscillation in the maximum pressure history, and the pressure amplitude of low frequency was much larger than the others. The pressure peak appeared after weak mode, and the stable, periodical unstable and weak modes were sequentially observed with pressure decay. A series of simulations of spinning detonations clarified that the unsteady mechanism behind the shock front depending on the activation energy.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년 추계학술대회논문집
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• pp.367-373
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• 2008

Spinning detonations propagating in a circular tube were numerically investigated with a one-step irreversible reaction model governed by Arrhenius kinetics. Activation energy is used as parameter as 10, 20, 27 and 35, and the specific heat ratio and the heat release are fixed as 1.2 and 50. The time evolution of the simulation results was utilized to reveal the propagation mechanism of single-headed spinning detonation. The track angle of soot record on the tube wall was numerically reproduced with various levels of activation energy, and the simulated unique angle was the same as that of the previous reports. The maximum pressure histories of the shock front on the tube wall showed stable pitch at Ea=10, periodical unstable pitch at Ea=20 and 27 and unstable pitch consisting of stable, periodical unstable and weak modes at Ea=35, respectively. In the weak mode, there is no Mach leg on the shock front, where the pressure level is much lower than the other modes. The shock front shapes and the pressure profiles on the tube wall clarified the mechanisms of these stable and unstable modes. In the stable pitch at Ea=10, the maximum pressure history on the tube wall remained nearly constant, and the steady single Mach leg on the shock front rotated at a constant speed. The high and low frequency pressure oscillations appeared in the periodical unstable pitch at Ea=20 and 27 of the maximum pressure history. The high frequency was one cycle of a self-induced oscillation by generation and decay in complex Mach interaction due to the variation in intensity of the transverse wave behind the shock front. Eventually, sequential high frequency oscillations formed the low frequency behavior because the frequency behavior was not always the same for each cycle. In unstable pitch at Ea=35, there are stable, periodical unstable and weak modes in one cycle of the low frequency oscillation in the maximum pressure history, and the pressure amplitude of low frequency was much larger than the others. The pressure peak appeared after weak mode, and the stable, periodical unstable and weak modes were sequentially observed with pressure decay. A series of simulations of spinning detonations clarified that the unsteady mechanism behind the shock front depending on the activation energy.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.407-408
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• 2006

Passenger safety is one of the most important considerations in the purchase of an automobile. A curtain-type air bag is increasingly adapted in deluxe cars for protecting passengers from the danger of side clash. Inflator housing is a main part of the curtain-type air bag system for supplying high-pressure gases to pump up the air bag-curtain. Although the inflator housing is fundamental in designing a curtain-type air bag system, flow information on the inflator housing is very limited. In this study, we measured instantaneous velocity fields of a high-speed flow ejecting from the inflator housing using a dynamic PIV system. From the velocity field data measured at a high frame-rate, we evaluated the variation of the mass flow rate with time. From the instantaneous velocity fields of flow ejecting from the airbag inflator housing in the initial stage, we can see a flow pattern of broken shock wave front and its downward propagation. The flow ejecting from the inflator housing was found to have large velocity fluctuations and the maximum velocity was about 700m/s. The velocity of high-speed flow was decreased rapidly and the duration of high-speed flow over 400m/s was maintained only to 30ms. After 100ms, there was no perceptible flow.