• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.21-21
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• 1998

추력방향 제어시스템 설계에 있어서 가장 기본적으로 요구되는 Requirement는 Rocket Motor의 추력, 요구되는 최대 Side Force, Rocket Motor의 외경, System의 총 구동시간, 구동후의 분리여부 등이다. 이러한 Requirement를 만족하기 위해서는 Nozzle 출구의 분출가스 물성치로부터 초음속 유동해석을 통하여 Vane 주위의 속도, 온도, 압력 분포를 구하고, Vane의 받음각 변화에 대한 Aerodynamic Force와 Moment를 계산하고, Side Force를 만족하는 최대 받음각의 결정, Torque를 만족하는 감속기와 Motor의 선정 및 Housing 기본 형상을 설계하였다. 금번 개발에서는 지상 시험용으로서 안전 계수를 Flight Model보다 약간 높게 설계하였으며, 작동 완료 후 System이 Nozzle로부터 떨어져나가는 분리시스템은 포함하지 않았다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.23-23
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• 1998

Jet Vane Type 추력방향제어 시스템의 구조적 안정성을 검토하기 위해 시스템의 해석을 Vane, Ablation & Bracket Interface, Nozzle flange & Housing Interface 및 Fastener의 세 부분으로 나누어 수행하였다. 해석을 위한 외력조건은 유동해석을 통해 얻어진 온도 및 압력분포에 근거하였으며, Vane의 응력해석을 위해서는 상용 Software인 Patran 및 Nastran이 사용되었다. 이번 연구는 Test Model 단계로서 충분한 강도의 고정 Housing이 사용되어, 이에 대한 해석은 수행되지 않았지만 추후 Flight Model 단계에서는 함께 고려되어질 것이며, 각 경우의 Margin of Safety값들을 도출하여 구조적 안정성을 검토하였다.

• Journal of Biosystems Engineering
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• v.7 no.2
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• pp.57-71
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• 1983

마찰식 정미기의 성능에 영향을 미치는 기계설계 및 작동상의 인자로는 스크린의 형태, 롤러의 형태, 롤러회전속도, 출구 저항 등 여러가지가 있다. 이러한 요인들에 대한 연구가 본 논문의 저자에 의해서 시리즈로 연구되어 왔으며, 본 연구는 그의 일환으로 스크린의 단면형상(6각, 8각, 12각 그리고 원통형), 스크린에 뚫려있는 슬랏의 기울기($15^{\circ}$, $30^{\circ}$, $45^{\circ}$ 그리고 $-45^{\circ}$), 그리고 출구 저항이 정백미의 질과 양, 정백효율 그리고 정백실내의 정백압력 등에 미치는 영향을 규명하기 위해 수행되었다. 이 실험에 사용된 공시 정미기는 임도정 공장에서 널리 사용되고 있는 흡입마찰식이었며, 사용된 시료는 밀양 23호인 통일계품종이었다. 각 처리마다 동력 소모량과 정백실내의 정백압력을 측정하기 위해서 "KYOWA" 스트레인 게이지 시스템(strain gauge system), 토오크 변환기, 압력변환기 등이 사용되었다. 본 실험 결과를 요약하면 다음과 같다. 1) 정백과정중에 정백실내의 정백압력은 입구에서 가장 높았고 출구쪽으로 갈수록 점차 감소하였다. 평균 정백압력도 순환 횟수에 따라서 변화 하였는데 첫번째 순환에서 가장 높았고 순환횟수가 증가함에 따라 감소하였다. 2) 본 실험에서 사용한 출구저항 수준은 출구저항 수준 1에서 요구되는 정백도의 백미를 얻기 위한 순환 횟수는 2회 이었고 출구저항 수준 2에서는 4회 이었는데, 이를 출구저항 수준이 정백압력, 정백율, 완전미수율 및 도정 효율에 가장 큰 영향을 주었다. 3) 스크린에 뚫려있는 슬랏 각도가 $15^{\circ}$에서 $45^{\circ}$로 증가함에 따라서 정백실내의 평균 정백압력은 감소하였고, 완전미수율과 도정 효율은 증가하였으나, 일반적으로 도정수율은 감소하는 경향을 보였다. $-45^{\circ}$의 슬랏 각도를 가진 스크린에서는 슬랏 각도 $15^{\circ}$인 스크린에서와 거의 비슷한 정백압력 수준을 나타냈으나 완전미와 정백미의 생산은 매우 낮았다. 4) 스크린 표면에 기다란 강편 (보통 "띠"라고 부름)을 붙인 원통과 12각형의 스크린에서는 강편을 붙이지 않은 6각형과 8각형 스크린에서 보다는 비교적 높은 정백압력을 나타냈다. 전자는 후자에 비해서 정백효율은 높았으나 완전미수율은 떨어졌다. 5) 정백실내에서 가장 낮은 정백압력을 나타낸 8각형 스크린은 높은 도정수율과 완전미수율을 가져왔으나 상대적으로 정백효율은 낮게 나타났다. 6) 정백실내의 반경 방향의 평균 정백압력($P_R$)과 완전미수율($Y_h$)은 다음과 같은 1차적인 역비례 관계가 있었으며(평균 정백압력 범위는 0.5-0.9kg/$cm^2$), $Y_h=-28.661P_R+84.860$ ($r^2=0.858$) 정백효율($Y_e$)과 정백압력($P_R$) 사이에는 다음과 같은 2차적인 관계가 존재함을 알 수 있었다. $Y_e=-597.5P_{R^2}+929.96P_R-210.15$ ($r^2=0.759$) 정백효율은 정백압력이 0.7-0.8kg/$cm^2$일 때 가장 높았으며, 이때 변이도 가장 심한 것으로 나타났다.

• Journal of the Korean Vacuum Society
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• v.16 no.4
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• pp.244-249
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• 2007

Deadweight piston gauge have been widely used as a fundamental instrument of precise pressure measurement because they are robust, accurate, potable, convenient to use and are able to realize the definition of pressure as farce per unit area. Basically, a deadweight piston gauge consists of a piston mounted vertically in a close-fitting cylinder filled with a gas and weights of known mass values. The pressure to be measured is applied to the base of the piston generating an upward vertical force, and is balanced by the downward gravitational force generated by weights. These instruments can be used to measure pressures above 10 kPa because of tare weights including piston. However, using a variable bell-jar pressure method and a newly developed weight loading device we can extend the application range of deadweight piston gauge to lower pressures. In this paper, we present the practical calibration results for two CDGs(Capacitance diaphragm gauge, MKS) with full-scale ranges of 1.33 kPa and 13.3 kPa, respectively.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.3
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• pp.1-7
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• 2002

An experimental study was conducted to investigate the effects of leading edge extension(LEX) on the surface prssure distribution over a delta wing in a subsonic wind tunnel. Freestream velocity was 40m/sec and Reynolds number per meter was 1.7x$10^6$ with total pressure of 101Pa and total temperature of 278K. LEX changed the surface pressure distribution on the wing dramatically. Comparing with the results without LEX, the peak of pressure distribution decreased on the front chordwise location but it turned to increase on the rear chordwise location with increase of the angle of attaci. The spanwise gradient of the pressure distribution also increased in the rear chordwise location. Without LEX, the peak of pressure distribution increased and decreased irregularly with increase of the angle of attack at each chordwise location, but LEX made it increased almost linearly with increase of the angle of attack at all of the chordwise locations.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.1
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• pp.68-75
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• 2015

In this paper, unsteady characteristics of pressure in solid rocket motor were analyzed by using response of pintle actuation, pressure and thrust data from ground test. Pressure and thrust in solid rocket motor can be controlled in real time by varying nozzle throat area with pintle, installed in the valve. Unsteady characteristics of pressure can be observed in this system occurred by various reasons. Two critical reasons, error of pintle actuation and ablation of center tube, are found and effects of each reason can be analyzed individually by re-prediction of pressure with response of pintle actuation and analyzing thrust to pressure ratio.

• The Journal of the Petrological Society of Korea
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• v.8 no.1
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• pp.24-33
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• 1999

Differential Strain Analysis (DSA) was performed to examine the characteristics of microcracks for the granites from two sites, Noeunri and Gunggiri. The results of the DSA are taken every 5 MPa for the first 50 MPa, then every 10 MPa to a pressure of 100 MPa, and then every 15 MPa to a pressure of 250 MPa. Differential strain was measured on core samples in three horizontal directions, using $45^{\circ}$ rosette strain gages, and one vertical direction. The gradients of cumulative crack strain curves in one vertical direction and three horizontal directions differed from one another, indicating anisotropic crack development in the sample. The magnitude of vertical cumulative crack strain was the highest, indicating that the microcracks from the studied rock are generally developed in horizontal direction. Under the pressure of 240 Mpa, vertical cumulative crack strains for samples N-1, N-2, G-1, and G-2 were $74{\times}l0^{-6}~820{\times}l0^{-6},\; 190{\times}l0^{-6}~460{\times}l0^{-6},\; 329{\times}l0^{-6}~836{\times}l0^{-6},\; 833{\times}10^{-6}~1,592{\times}l0^{-6}$, respectively. Under the pressure of 25O MPa, volumetric crack strains for Gunggiri and Noeunri ranged from $1,804{\times}10^{-6}\; to\; 3,936{\times}10^{-6}\; and \;from,\; 1, 125{\times}10^{-6}\; to\; 1,457{\times}10^{-6}$, respectively. Therefore, the amount of microcrackes produced were more distributed in Gunggiri than Noeunri. The ratio of a maximum crack strain to a minimum crack strain was calculated to find the orientations between microcracks and the rift plane of the granites. Generally, the ratio has very high values ranging from 2.42 to 3.43, which suggests most microcracks to be intragranular cracks with the regular orientations. These results indicate that the preferred orientations of microcracks in the granites were almost parallel to the rift plane of the granites.

• Journal of Advanced Marine Engineering and Technology
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• v.37 no.4
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• pp.358-367
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• 2013

In the present paper, we apply a porous modelling technique to accurately predict the pressure drop through the strainer by replacing all or some of the filter composed of perforated plates with porous media and there imposing the streamwise and transverse loss coefficients required according to the Forchheimer law and then confirm its effectiveness. At first, the streamwise coefficient is obtained by performing a simple simulation on the pipe flow mimicking the hole flow. Subsequently, the transverse coefficient is obtained by setting a unit pattern to have common flow loss characteristics with the repeated shape patterns in the filter, then performing numerical simulations on the prototype and porous model of the unit shape pattern, and finally comparing their results of pressure drop. To validate the applied modeling technique, we perform the numerical simulation with the two specified loss coefficients on a whole shape of strainer and compare the modeling results with those of the corresponding prototype numerical simulation. Comparison indicates that the modeling technique can predict the pressure drop and flow characteristics comparatively accurately and save the number of nodes closely related to the computational cost (CPU and memory) by about 3~4 times compared with the prototype simulation.

• Fire Science and Engineering
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• v.22 no.3
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• pp.272-277
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• 2008

This study is performed for propose that exactly equivalent length of TBP in the applied at water-based fire protection system. For predict the measuring position of equivalent length, we determined the measuring position using the FVM about pressure drop of TBP. For the reckon of the exact about measured value we compared with the result of FVM and we knew the similar value each other. Using the results we proposed the friction loss measuring position that inlet of main dirction is 20 times of appellation diameter in main pipe, outlet of main dirction is 10 times of appellation diameter in main pipe and outlet of branched direction is 20 times of appellation diameter.

• Transactions of the Korean Society of Mechanical Engineers
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• v.10 no.1
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• pp.15-24
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• 1986

Pressure trasients must deal with safety problem of system. For identification of physical situation that can and method of limiting surges are essential consideration in sucessful design. The finite difference equation by method of characteristics are derived from the governing equation of unsteady flow in a pipe, and solved by using boundary condition derived. A computer program which can simulate general hydraulic system is developed by using finite difference equations and boundary conditions derived. The sumulated resulted by developed computer program are in fair agreement with experiment result.