• 한국전자파학회논문지
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• 제22권1호
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• pp.81-88
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• 2011

본 논문은 비선형 소자 탐지기용 광대역 스파이럴 안테나의 설계를 제안한 것이다. 방사면 위의 스파이럴 소자뿐만 아니라 방사면 중심부에 위치한 방사 소자인 타원형 패치가 스파이럴 안테나의 광대역화를 위하여 설계되었다. 또한, 그라운드면 위에 스파이럴 슬릿을 삽입함으로써 다중 공진을 일으키는 안테나 그라운드 구조가 제안되었다. 제안된 안테나의 높은 지향성과 고이득을 실현하기 위해, Fr4-epoxy로 만든 캐비티 벽과 금속캡이 설계에 고려되었다. 그 결과, 금속 캡을 가진 안테나의 계산된 이득은 금속 캡이 없는 안테나의 이득과 비교하여 약 3 dBi 개선되었으며, -z축 방향으로의 측정된 주 빔 지향성도 계산 결과와 잘 일치하였다. 설계 주파수 대역에서 측정된 축비도 -z축을 기준으로 ${\pm}45^{\circ}$의 범위에서 원편파를 만족하였으며, 예상과 잘 일치하였다.

• 멤브레인
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• 제13권1호
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• pp.37-46
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• 2003

하전된 멤브레인 미세기공으로 유체가 흐르는 경우는 계면동전기 효과가 작용하게 된다. 비선형 Poisson-Boltzmann 전기장과 흐름에 의해 유발되는 전기장 사이의 정전상호작용을 운동방정식의 외부작용 힘으로 고려하였다. 유한차분법으로 정전위 분포를 우선 산출하고, 이어서 Green 함수로 슬릿형 기공에 대한 Navier-Stokes 식의 해석해를 구하였다. 계면동전기적 유동에 의한 흐름전위를 관련된 물리화학적 인자들의 함수로 유도되는 해석적인 명확한 표현으로 제시하였다. 전기이중층, 표면전위, 그리고 기공벽면의 하전조건의 영향에 따른 유속분포와 흐름전위 변화를 고찰하였다 계산결과, 전기이중층 두께나 표면전위가 증가함에 따라 평균유속은 감소하는 반면에 흐름전위는 증가하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.91-93
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• 2003

A comprehensive numerical study is carried out to investigate for the understanding of the flow evolution and flame development in a supersonic combustor with normal injection of ncumally injecting hydrogen in airsupersonic flows. The formulation treats the complete conservation equations of mass, momentum, energy, and species concentration for a multi-component chemically reacting system. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations and detailed chemistry of H2-Air is considered. It also accommodates a finite-rate chemical kinetics mechanism of hydrogen-air combustion GRI-Mech. 2.11[1], which consists of nine species and twenty-five reaction steps. Turbulence closure is achieved by means of a k-two-equation model (2). The governing equations are spatially discretized using a finite-volume approach, and temporally integrated by means of a second-order accurate implicit scheme (3-5).The supersonic combustor consists of a flat channel of 10 cm height and a fuel-injection slit of 0.1 cm width located at 10 cm downstream of the inlet. A cavity of 5 cm height and 20 cm width is installed at 15 cm downstream of the injection slit. A total of 936160 grids are used for the main-combustor flow passage, and 159161 grids for the cavity. The grids are clustered in the flow direction near the fuel injector and cavity, as well as in the vertical direction near the bottom wall. The no-slip and adiabatic conditions are assumed throughout the entire wall boundary. As a specific example, the inflow Mach number is assumed to be 3, and the temperature and pressure are 600 K and 0.1 MPa, respectively. Gaseous hydrogen at a temperature of 151.5 K is injected normal to the wall from a choked injector.A series of calculations were carried out by varying the fuel injection pressure from 0.5 to 1.5MPa. This amounts to changing the fuel mass flow rate or the overall equivalence ratio for different operating regimes. Figure 1 shows the instantaneous temperature fields in the supersonic combustor at four different conditions. The dark blue region represents the hot burned gases. At the fuel injection pressure of 0.5 MPa, the flame is stably anchored, but the flow field exhibits a high-amplitude oscillation. At the fuel injection pressure of 1.0 MPa, the Mach reflection occurs ahead of the injector. The interaction between the incoming air and the injection flow becomes much more complex, and the fuel/air mixing is strongly enhanced. The Mach reflection oscillates and results in a strong fluctuation in the combustor wall pressure. At the fuel injection pressure of 1.5MPa, the flow inside the combustor becomes nearly choked and the Mach reflection is displaced forward. The leading shock wave moves slowly toward the inlet, and eventually causes the combustor-upstart due to the thermal choking. The cavity appears to play a secondary role in driving the flow unsteadiness, in spite of its influence on the fuel/air mixing and flame evolution. Further investigation is necessary on this issue. The present study features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the previous works. In particular, the oscillatory flow characteristics are captured at a scale sufficient to identify the underlying physical mechanisms. Much of the flow unsteadiness is not related to the cavity, but rather to the intrinsic unsteadiness in the flowfield, as also shown experimentally by Ben-Yakar et al. [6], The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The work appears to be the first of its kind in the numerical study of combustion oscillations in a supersonic combustor, although a similar phenomenon was previously reported experimentally. A more comprehensive discussion will be given in the final paper presented at the colloquium.

• 대한기계학회논문집B
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• 제33권9호
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• pp.666-673
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• 2009

The turbulent swirling flow field characteristics of a gun-type gas burner with a combustion chamber were investigated under the cold flow condition. The velocities and turbulent quantities were measured by hot-wire anemometer system with an X-type probe. The turbulent swirling flow field in the edge of a jet seems to cause a recirculation flow from downstream to upstream due to the unbalance of static pressure between a main jet flow and a chamber wall. Moreover, because the recirculation flow seems to expand the main jet flow to the radial and to shorten it to the axial, the turbulent swirling flow field with a chamber increases a radial momentum but decreases an axial as compared with the case without a chamber from the range of about X/R=1.5. As a result, these phenomena can be seen through all mean velocities, turbulent kinetic energy and turbulent shear stresses. All physical quantities obtained around the slits, however, show the similar magnitude and profiles as the case without a chamber within the range of about X/R=1.0.

• 대한기계학회논문집B
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• 제22권9호
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• pp.1229-1237
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• 1998

Experiments of shock-wave/turbulent boundary layer interaction were conducted by using a supersonic wind tunnel. Nominal Mach number was varied in the range of 1.6 to 3.0 by means of different nozzles. The objective of the present study is to investigate the effects of boundary layer suction on normal shock-wave oscillations caused by shock wave/boundary layer interaction in a straight duct. Two-dimensional slits were installed on the top and bottom walls of the duct to bleed turbulent boundary layer flows. The bleed flows were measured by an orifice. The ratio of the bleed mass flow to main mass flow was controlled below the range of 11 per cent. Time-mean and fluctuating wall pressures were measured, and Schlieren optical observations were made to investigate time-mean flow field. Time variations in the shock wave displacement were obtained by a high-speed camera system. The results show that boundary layer suction by slits considerably reduce shock-wave oscillations. For the design Mach number of 2.3, the maximum amplitude of the oscillating shock-wave reduces by about 75% compared with the case of no slit for boundary layer suction.

• The Korean Journal of Physiology
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• 제11권2호
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• pp.67-71
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• 1977

This study was undertaken to investigate the effect of cingulate cortical ablation upon gastric secretion and its components in rats. 23 male rats were divided into the cingulate(N=9) and the operated control(N= 14) groups. Cingulate cortex was ablated through a slit-shaped opening(1 mm in width, 5 mm in length) which was made symmetrically on both sides of, and parallel to, the sagittal suture by removing a bone flap from frontal bone on each side. In the operated control group, the surgical procedure was ended by the removal of the bone flap. Under light ether anesthesia, experimental animals were placed in a restraining jacket of fine mesh wire and gastric juice was collected for 5 hours via a canula which had been inserted through the anterior abdominal wall into the antral portion of the lumen of the stomach. Volume of the gastric juice was measured, and total acid output and free acid output were titrated with 0.04 N NaOH solution by using phenolphthalein and Topfer's reagent at indicator, and chloride ion output was estimated by means of chloridometer. Results obtained were that volume, total acid output, free acid output and chloride ion output of the gastric juice were higher significantly in the cingulate group than in the operated control group. It is inferred from the above results that the cingulate cortex exerts a fascilitatory influence upon gastric secretion and acid output in rats.

• 동력기계공학회지
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• 제10권4호
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• pp.17-24
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• 2006

The turbulent flow field characteristics of a gun-type gas burner with and without a duct were investigated under the isothermal condition of non-combustion. Vectors and mean velocities were measured by hot-wire anemometer system with an X-type hot-wire probe in this paper. The turbulent flow field with a duct seems to cause a counter-clockwise recirculation flow from downstream to upstream due to the unbalance of static pressure between a main jet flow and a duct wall. Moreover, the recirculation flow seems to expand the main jet flow to the radial and to shorten it to the axial. Therefore, the turbulent flow field with a duct increases a radial momentum but decreases a axial momentum. As a result, an axial mean velocity component with a duct above the downstream range of about X/R=1.5 forms a smaller magnitude than that without a duct in the inner part of a burner, but it shows the opposite trend in the outer part.

• 센서학회지
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• 제27권6호
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• pp.386-391
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• 2018

To analyze the film cooling in a liquid rocket engine, it is necessary to understand the characteristics of the wall-impingement liquid film. We designed an optimal two-dimensional device for measuring the thickness of the liquid film thickness. This device quantitatively measures the liquid-film thickness distribution. In previous liquid-film thickness measuring devices, the liquid film was formed over the entire area of the sensor. However, its formation depended on injection conditions. To compensate for this, optimal resistors are selected. Additionally, saturation variations with partial saturation are analyzed. Furthermore, calibration using the enhanced plate method is conducted with improvements in spatial resolution. The device designed here can be used to analyze the properties of an impingement liquid film with a slit injector. This study can be used for film-cooling analysis in liquid rocket engines.

• Journal of the Korean Wood Science and Technology
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• 제39권4호
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• pp.318-325
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• 2011

현장에서 시공성이 용이함과 동시에 강도 성능이 뛰어난 steel bar를 이용한 리기다소나무 옹벽을 제작하여 내력평가를 실시하였다. Steel bar를 이용한 목재옹벽은 횡목 4단과 종목 3단으로 적층하였으며, 높이 770 mm, 길이 2,890 mm, 폭 782 mm로 제작하였다. 적층 방법은 18 mm로 선공한 최상단과 최하단 횡목을 Steel bar에 삽입하며, 깊이 64 mm, 폭 18 mm의 슬릿을 낸 나머지 횡목과 종목을 Steel bar에 끼워 넣어 적층하였다. 완성 된 옹벽은 수평 재하 시험을 통한 내력 평가와 화상처리(AlCON 3D OPA-PRO system)를 통하여 구조물의 변형을 측정하였다. Steel bar옹벽에는 1개의 긴 횡목과 2개의 종목으로 구성된 접합부(Type-A)와 반턱으로 이음된 2개의 짧은 횡목이 2개의 종목으로 구성된 접합부(Type-B)가 공존하며, 이들을 각각 3개씩 제작하여 접합부의 압축형 전단내력 평가를 실시하였다. Steel bar옹벽의 수평 재하 시험결과 정각재 목재옹벽(박준철 등, 2010)보다 1.6배 이상의 강도를 나타냈으며, 이때 목재와 접합부의 파단은 발생하지 않았다. 접합부의 압축형 전단 내력 실험결과 Type-A의 평균 최대 하중은 130.13 kN, Type-B의 평균 최대 하중은 130.6 kN으로 측정되었다. 실험 결과 Steel bar를 이용한 목재옹벽은 정각재 목재옹벽보다 시공성이 우수하며 강도 또한 높게 측정되었다.

• 한국지반공학회논문집
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• 제18권4호
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• pp.339-347
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• 2002

보강토 옹벽에 체인을 보강재로 사용한 경우의 인발저항력 평가를 위한 현장실험을 실시하였다. 실험에서는 횡방향 부재로 강봉이나 L-형 강재앵글을 고려하였으며, 체인의 길이(20m, 2.5m 그리고 3.0m), 보강재의 조합(체인단독, 체인＋강봉 그리고 체인＋앵글) 그리고 설치위치 등을 다르게 하여 총 80개소에 대해서 인발실험을 실시하였다. 체인 또는 체인＋강봉의 경우, 최대 변위는 평균 150mm였으며, 인발하중은 지속적으로 증가하다가 체인의 극한강도에 도달하면 파단(인장파괴)되는 것으로 나타났다. 그러나 체인에 L-형 앵글을 조합한 경우에는 최대변위가 평균 100mm정도로서 변위 억제에 큰 효과가 있는 것으로 나타났다. 현장에서 측정된 항복 인발하중값을 이론값과 비교했을 때는 보강 방법 또는 연직응력에 따라서 현장 측정값이 이론값 보다 약 1.2~3배정도 큰 것으로 나타났으며, 체인의 길이, 연직하중의 크기, 횡방향 부재의 조합에 따라서 항복 인발하중의 크기는 변화하는 것으로 나타났다. 그러나 강봉과 L-형 앵글사이에 차이는 현저하지 않았다. 체인을 보강재로 사용하는 경우 기존의 이론식을 적용한 설계나 시공은 안전측으로 나타났으나, 체인의 인발 저항력이 너무 과소 평가되어 있다고 판단되었다.