• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.235-238
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• 2004

In the present study, the stability of turbopump through the rotor dynamics was analyzed with the location analysis method of the pole of characteristic equation for stability analysis of LRE and the design guideline for turbopump was presented according to design requirements of the LRE.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.5-8
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• 2004

In this study, the fundamental design procedure for the Smart UAV fuel supply system was set up, and the preliminary design was peformed to meet the vehicle system requirements. The fuel system layout was determined through consideration of vehicle system requirements, and then fuel tank layout, design of components such as booster pump, jet pump, pipe, vent system, weight estimation, etc. were carried out.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.2
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• pp.54-61
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• 2005

In this study, the fundamental design procedure for the Smart UAV fuel supply system was set up, and the preliminary design was performed to meet the vehicle system requirements. The fuel system layout was determined through consideration of vehicle system requirements, and then fuel tank layout, design of components such as booster pump, jet pump, pipe, vent system, weight estimation, etc. were carried out. Based on this fuel system layout, operational reliability analysis was carried out.

• Journal of the Institute of Electronics Engineers of Korea SD
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• v.47 no.2
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• pp.94-99
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• 2010

This paper presents a charge pump architecture for correcting the current mismatch due to the PVT variation. In general, the current mismatch of the charge pump should be minimized to improve the phase noise and spur performance of the PLL. In order to correct the current mismatch of the charge pump, the current difference is detected by the replica charge pump and fed back into the main charge pump. This scheme is very simple and guarantees the high accuracy compared with the prior works. Also, it shows a good dynamic performance because the mismatch is corrected continuously. It is implemented in 0.13um CMOS process and the die area is $100{\mu}m\;{\times}\;160{\mu}m$. The voltage swing is from 0.2V to 1V at supply voltage of 1.2V. The charging and discharging currents are $100{\mu}A$, respectively and the current mismatch due to the PVT variation is less than 1%.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.72-80
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• 2004

LOX pump is one of the sub-assemblies constructing turbopump unit. In the current study, static structural analysis on such rotating parts as impeller and inducer has been carried out. Three major factors which can affect the structural stability of the rotating parts of LOX pump, are temperature, pressure, and centrifugal force. The effect of each factor was preliminarily investigated, then the analysis under the consideration of the combined loading conditions has been carried out. The major factor that affects the structural stability was proved to be temperature. The analyses of the combined cases showed that the designed impeller and inducer had reasonable safety margins, which means that the impeller and the inducer will be stable in static structural strength. Although there was no problem in the structural strength of the impeller and the inducer, a model analysis should be followed in order to verify the interference between the rotating part and the inner surface of casing.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.35-41
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• 2013

Torque characteristics of a turbopump turbine was analyzed using the turbine performance test result. Specific torque of the subject turbine could be expressed as a linear function of corrected rotor speed at a fixed pressure ratio and it has been confirmed by the test result. It also found that corrected rotor speed-specific torque characteristics does not change anymore if the turbine pressure ratio is set bigger than a certain value. Using the turbine torque characteristics and pyro-starter performance test results, rotational speed development behavior of the turbopump was predicted. Prediction revealed that the lap time reaching 50% of turbopump design speed is less than 0.7 second. Effect of the thermal loss between pyro-starter and turbopump was negligible.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.11 no.3
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• pp.391-400
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• 1999

The efficiency and capacity of an air source heat pump system decrease as the ambient temperature drops. One strategy of avoiding the decrease of the efficiency and capacity in air source heat pump system is to switch to another thermal energy source. Water can be a good candidate for the heat source. This paper presents the results of the performance analysis of heat pump system with a single unit dual source(SUDS) evaporator The heat exchanger combines two separated evaporators into a single evaporator and the object of the SUDS evaporator is to recover energy from dual heat sources, i.e. air and water. Simulation program is developed for the dual source heat pump system with a SUDS evaporator and experimental data are obtained and compared with the simulation results. Differences in heating capacity and COP are 7% and 8% respectively. Simulation results are in good agreement with the test results. Therefore, the developed program is effectively used for the design and performance prediction of the dual source heat pump system with a SUDS evaporator.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.4-10
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• 2012

Torque characteristics of a 75-tonf turbopump turbine was analyzed using the turbine performance test result. Specific torque of the subject turbine could be expressed as a linear function of corrected rotor speed at a fixed pressure ratio and it has been confirmed by the test result. It also found that corrected rotor speed-specific torque characteristics does not change anymore if the turbine pressure ratio is set bigger than a certain value. Using the turbine torque characteristics and pyro-starter performance test results, rotational speed development behavior of the turbopump was predicted. Prediction revealed that the lap time reaching 50% of turbopump design speed is less than 0.7 second. Effect of the thermal loss between pyro-starter and turbopump was negligible.

• Journal of IKEEE
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• v.28 no.1
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• pp.78-89
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• 2024

PMIC chips based on a BCD process used in automotive semiconductors require multi-time programmable (MTP) intellectual property (IP) that does not require additional masks to trim analog circuits. In this paper, MTP cell size was reduced by about 18.4% by using MTP cells using PMOS capacitors (PCAPs) instead of NMOS capacitors (NCAPs) in MTP cells, which are single poly EEPROM cells with two transistors and one MOS capacitor for small-area MTP IP design. In addition, from the perspective of MTP IP circuit design, the two-stage voltage shifter circuit is applied to the CG drive circuit and TG drive circuit of MTP IP design, and in order to reduce the area of the DC-DC converter circuit, the VPP (=7.75V), VNN (=-7.75V) and VNNL (=-2.5V) charge pump circuits using the charge pumping method are placed separately for each charge pump.

• Proceedings of the Korean Nuclear Society Conference
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• 1995.05a
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• pp.596-601
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• 1995

신뢰도 분석 방법을 이용하여 습식 사용후핵연료 중간저장시설의 냉각계통에 대한 최적 설계조건을 도출하기 위한 연구를 수행하였다. 먼저 고장수목 분석을 통한 설계 취약점을 평가하여 21개의 설계대안을 도출하였고, 최종적으로 설계대안에 대한 건설비 용, 계통신뢰도 분석 및 확률론적 안전기준을 고려한 비용효과 분석을 실시하였다. 설계 대안들 중에서 100% 루프 다중설계, 루프당 한 개의 펌프 사용, 안전등급 부여 및 주 루프에서 정화계통이 분리된 경우가 최적설계안으로 나타났다. 여기서 적용된 방법론은 유사시설의 최적설계에 유용하게 응용될 수 있을 것으로 사료된다.