• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.150-161
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• 2005

A test was performed to collect the data to validate an analytic method for vent hole sizing on the nose fairing of a launch vehicle. The bake-out chamber at KARI was used to simulate the ambient pressure drop, and pressure difference data were collected for a model with various kinds of vent holes which was installed in the chamber. The characteristics of the test facility and measurement equipments were evaluated for the measurement of the transient behaviors. The measured data were processed in consideration of the characteristics of the facility and equipments, and the effects of vent hole size and configuration on the pressure variation in the model were analyzed based on the data.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.42-49
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• 2021

As a measure of susceptibility on the combustion instability, thermo-acoustic instabilities in rocket combustion system was considered for the estimation of the operational stability margin. Growth rate, which governs the asymptotic stability behavior of the system, was determined from the dynamic data measured during combustion tests in order to understand the dynamic characteristics of combustor system. Frequency transform technique was first applied to determine the system parameters such as growth rate and/or damping coefficient for an interested mode from the time series pressure data, and the PDFs of pressure amplitude were extracted from the amplitude envelope of pressure oscillation for the stochastic analysis.

• Proceedings of the Korean Vacuum Society Conference
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• 2011.02a
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• pp.356-356
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• 2011

챔버 내부의 압력은 gauge가 달려 있는 몇몇 지점에만 국한되어 읽을 수 있었기 때문에 gauge를 이용한 압력 측정을 통해 보다 상세한 진공도를 구하기란 쉽지 않다. 챔버 내부의 압력은 빔 운전에 적합한 초고진공을 유지하여야 하고, 균일하여야 하므로 신뢰 할 수 있는 방법으로 진공도를 정확히 계산해 볼 필요가 있다. 그리하여 압력에 영향을 미치는 여러 가지 진공 시스템 내부의 요소인 Outgassing, 배기속도, 컨덕턴스, 압력 등을 mass balance equation을 이용해 수식화 하여 정리한다. 이 수식을 가지고 FEA(Finite element analysis)프로그래밍을 이용해 진공도를 계산한다. FEA 프로그래밍에 쓰이는 프로그램은 Matlab, excel을 이용하였다. 이 프로그래밍 결과에 따라 Pressure Profile을 작성 하고, 시간이 변함에 따라 진공도가 어떻게 변하는지 실제로 계산하여 time constant를 구한다. 이 값들을 챔버를 가지고 측정한 데이터와 비교하여본다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.809-813
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• 2010

For the purpose of developing a modeling technique for reduced-order dynamics of thermoacoustic instability, we constructed an electrically heated Rijke tube and measured the pressure oscillation inside the tube. Analysing the measured pressure data showed that the instability generated three major oscillation modes, among which the first mode frequency quite well matches the result from a rough acoustic analysis. As a continuing research, a data-based modeling technique for the thermoacoustic instability will be developed in the near future.

• Journal of the Korea Society of Computer and Information
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• v.15 no.4
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• pp.99-106
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• 2010

In this paper, we propose an industrial fluid monitoring system which performs the flow control function and monitors fluid pressure transmitted from MFC(Mass Flow Controller) unit. This system consists of MFC unit, channel device, and monitoring management software. MFC unit transmits the measured data of the fluid pressure to the channel device which would provide the input/output interface between management software, monitoring and MFC unit. The monitoring and management software control and analyze by monitoring real time measurements of fluid pressure from each channel of MFC unit. This software can process 20 channels and 0.1 monitoring cycle which gives 200 data measurement per second (i.e., 720,000 data/hour). At this time, the storage space increases in proportion to the rise of input data. This growth of data and storage space makes loss of data access efficiency. Therefore, it demands the implementation by sensing scheme of change scope and data, which can effectively manage the data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.1
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• pp.1-9
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• 2014

The present study was conducted by using fast-responding PSP technique to measure the surface pressure on a small-scale rotor blade in hover. Also, the study was performed to verify the accuracy and investigate its possibility of PSP application for rotor blade pressure measurement. Pulsed laser which has 532 nm wavelength was used as a light source. Lifetime measurement technique was applied. Also, the coated paint on a rotor blade was porous PSP which has faster response time than conventional PSP. The blades had NACA0012 airfoils. The length of rotor blade was 340 mm and chord was 40 mm with rectangular shape 1 set, and 4 sets had several tip sweepback angles. The measured results qualitatively showed that the upper surface pressure decreases with increasing the collective pitch angle. Quantitative pressure coefficients of PSP results were higher approximately 0.4 to 0.7 than the pressure tap data of the NASA experiment.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.10
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• pp.1513-1519
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• 2010

Recently, on-line process monitoring systems using sensors are being extensively used to produce highquality products. However, the difficulty in installing the sensors within the mold in the cases of micro-molds, optical molds, and molds with complex structures is a serious disadvantage of such process monitoring systems. In this study, the quantitative index of a process monitoring system was evaluated with the mold cavity pressure and the nozzle pressure for the injection molding machine. In order to evaluate the effect of the nozzle pressure, we performed correlation analysis for the weight of the molded product. We also examined the control characteristics of the injection molding machine by analyzing the effect of multistage injection speed, holding pressure, and injection pressure limit on the process monitoring data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.321-327
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• 2008

Performance characteristics of the axi-symmetric supersonic exhaust diffuser (SED) with a second throat are numerically investigated. Computational strategy repeats those for a straight exhaust diffuser with zero-secondary flows. Renolds-Average Navier-Stokes equations with a standard ${\kappa}-{\varepsilon}$ turbulence model incorporated with standard wall function are solved to simulate the diffusing evolutions of the nozzle plume. The methodology is validated with accuracy. To predict the improvement of starting performance by second throat diffuser, diffuser characteristic curve due to the SED equipped with the second throat is speculated with respect to that of a straight area type as a function of nozzle stagnation pressure. Principal physics caused by the of the second throst is also addressed in terms of a second throat area ratio.

• Proceedings of the KAIS Fall Conference
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• 2010.05b
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• pp.988-991
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• 2010

본 연구는 직접 연료분사 가솔린 엔진에 장착되는 고압연료 인젝터의 연료공급 특성에 대한 것으로, 두 종류 GDI 인젝터의 분무가시화 실험을 수행하였고, 분무특성을 분석하였다. 가시화 실험을 통하여 인젝터 끝단 분사 초단부근 연료거동을 확인하였고, 인젝터의 특성인 도달거리와 관통력을 확인하였으며, 분위기 압력의 변화에 따른 분무특성을 고려하여 실험을 수행하였다. 두 인젝터 모두 분위기 압력이 증가함에 따라 도달거리와 분사각이 감소하였다. B type의 인젝터 보다 A type의 인젝터가 분위기 압력에 민감한 것으로 나타났다. 본 연구를 통하여 분위기 압력의 변화에 따른 분무거동의 변화를 확인 하였으며 직접 분사인젝터의 엔진적용을 위한 기초 분무 데이터를 확보하였다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.9
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• pp.915-921
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• 2012

In this study, we propose a new method for estimating the IMEP using difference pressure, which is the pressure difference between the cylinder pressure and the motoring pressure. The estimated IMEP, denoted as $IMEP_{diff}$, optimizes the theoretical IMEP calculation range based on the fact that the difference pressure exists between the start and the end of combustion. $IMEP_{diff}$ is verified to have a high linear correlation with IMEP with $R^2$ of 0.9955. The proposed method can estimate the IMEP with 21% of the cylinder pressure data and 31% of the calculation effort compared to the theoretical IMEP calculation method, and therefore, it has great potential for real-time implementations. The estimation and control performance of $IMEP_{diff}$ is validated by engine experiments, and by controlling $IMEP_{diff}$, the torque variation between the cylinders was reduced.