• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2012년도 추계학술대회 논문집
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• pp.407-408
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• 2012

• 대한전기학회:학술대회논문집
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• 대한전기학회 2007년도 심포지엄 논문집 정보 및 제어부문
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• pp.307-308
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• 2007

At present, there are unnecessary electrical consumes and a lot of fuel-losses by the vaporized gas due to the rising of fuel temperature because the fuel pump of the fuel supply system rotates regularly regardless to the driving condition. In this paper, we designed the multi-step controller for controlling fuel pump to supply fuel according to RPM of each moment by measuring the real time RPM of the engine at ECU of the vehicle. Also, it can judge the existence or nonexistence of disorder by measuring the pressure of the fuel supply line, in case of abnormal state, it can supply the fuel intelligently by changing the mode to self-compensation mode.

• 한국산업융합학회 논문집
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• 제24권4_2호
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• pp.475-480
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• 2021

The purpose of this study is to obtain the natural frequency of fuel supply pipes for vehicle engines through modal analysis and testing and compare the resulting values to ensure the reliability of the analysis. In other words, in this study, we obtain the unique frequency of the fuel pipe of the vehicle engine through analysis and testing and compare its results. Comparing the natural frequency obtained through analysis and testing, the first and third vibration modes obtained accurate natural frequency results of less than 1% and very similar results of less than 5% maximum error over the fourth vibration modes. These results are determined that if design changes of fuel pipes are made depending on the vehicle in the future, there will be no problem in obtaining the natural frequency of pipes that have been changed by analysis. Through future analysis and testing, durability and stability evaluation of connections of fuel supply pipes for vehicle engines will be carried out.

• 한국항공운항학회지
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• 제21권2호
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• pp.1-6
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• 2013

In high-speed vehicle, selection of fuel, configuration of components and cooling system are required to solve the heating issue by aerodynamic heating and inner combustion process. This subsystem consists of fuel tank, supply pump, various control valve, heat exchanger, including reactor, connecting line, adiabatic structures and insulations. In this paper, applicable fuel property is considered at flight characteristic of hypersonic vehicles. In this regard, current state of fuel/cooling system technology is identified.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2009년도 춘계학술대회 논문집
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• pp.636-639
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• 2009

Fuel consumption measurement of Hydrogen fuel cell vehicle is considerably different form internal combustion engine vehicle such as carbon balance method. A practical method of fuel Consumption measurement has been developed for Hydrogen fuel cell vehicles. There are three method of hydrogen fuel consumption testing, gravimetric, PVT(Pressure, Volume and temperature), and Coriolis mass flow, all of which necessitate physical measurements of the fuel supply. The purpose of this research is to measure the fuel consumption of hydrogen fuel cell vehicles on chassis-dynamometer and to give information when the research is intended to develop method to measure hydrogen fuel consumption.

• 자동차안전학회지
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• 제13권4호
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• pp.73-80
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• 2021

Recently, Korea has established a plan for the supply of hydrogen vehicles and is promoting the expansion of the supply. Risk factors for hydrogen vehicles are hydrogen leakage, jet fire, and explosion. Therefore Safety measures are necessary for this hazard. In addition, risks in semi-closed spaces such as tunnels, underground roads, and underground parking lots should be analyzed. In this study, an explosion experiment was conducted on a hydrogen tank used in a hydrogen vehicle to analyze the risk of a hydrogen vehicle explosion accident that may occur in a semi-closed space. As results, the effect on the structure and the human body was analyzed using the overpressure and impulse values for each distance generated during the explosion.

• 한국수소및신에너지학회논문집
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• 제23권3호
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• pp.250-255
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• 2012

In this paper, the development and performance analysis of a fuel cell-powered unmanned aerial vehicle is described. A fuel cell system featuring 1 kW proton exchange membrane fuel cell combined with a highly pressurized fuel supply system is proposed. For the higher fuel consumption efficiency and simplification of overall system, dead-end type operation is chosen and each individual system such as purge system, fuel supply system, cooling system is developed. Considering that fluctuation of exterior load makes it hard to stabilize fuel cell performance, the power management system is designed using a fuel cell and lithium-ion battery hybrid system. After integration of individual system, the performance of unmanned aerial vehicle is analyzed using data from flight and laboratory test. In the result, overall system was properly operated but for more duration of flight, research on weight lighting and improvement of fuel efficiency is needed to be progressed.

• 한국수소및신에너지학회논문집
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• 제14권3호
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• pp.236-246
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• 2003

This paper focuses on developing a model of a PEM fuel cell stack and to integrate it with realistic model of the air supply system for fuel cell vehicle application. The fuel cell system model is realistically and accurately simulated air supply operation and its effect on the system power and efficiency using simulation tool Matlab/Simulink. The Peak performance found at a pressure ratio of 3, and it give a 15mV increase per cell. The limit imposed is a minimum SR(Stoichiometric Ratio) of 2 at low fuel cell load and 2.5 at high fuel cell load.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.5-13
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• 2017

한국형발사체 발사를 위하여 나로우주센터에 제 2발사대가 구축될 예정이며 연료공급설비 역시 새롭게 설치된다. 한국형발사체 발사대시스템의 연료공급설비는 나로호 발사대의 설계를 기본 바탕으로 하였다. 하지만 한국형발사체는 나로호 또는 시험발사체와는 달리 3단형 발사체이기 때문에 연료 이송펌프 1대로 1, 2, 3단의 발사체 연료 탱크로 연료를 공급해야한다. 유동해석을 통해 충전 시나리오를 선정하는 과정에서 펌프 토출압력의 급격한 상승 문제를 확인하였다. 이는 오리피스타입의 유량제어방식으로 각 단의 충전모드 전환에 따른 유량변화에 대해 리턴유량이 능동적으로 대응할 수 없기 때문에 발생하였다. 이 문제를 해결하기 위해 다양한 경우에 대해 유동해석을 통해 accumulator 설치와 각 단의 충전모드 전환 순서를 적절히 조정함으로써 안정적으로 공급할 수 있음을 확인하였다.

• 한국추진공학회지
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• 제22권5호
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• pp.132-140
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• 2018

한국형발사체 발사를 위하여 나로우주센터에 제 2발사대가 구축될 예정이며 연료공급설비 역시 새롭게 설치된다. 한국형발사체 발사대시스템의 연료공급설비는 나로호 발사대의 설계를 기본 바탕으로 하였다. 하지만 한국형발사체는 나로호 또는 시험발사체와는 달리 3단형 발사체이기 때문에 연료 이송펌프 1대로 1, 2, 3단의 발사체 연료 탱크로 연료를 공급해야한다. 유동해석을 통해 충전 시나리오를 선정하는 과정에서 펌프 토출압력의 급격한 상승 문제를 확인하였다. 이는 오리피스타입의 유량제어방식으로 각 단의 충전모드 전환에 따른 유량변화에 대해 리턴유량이 능동적으로 대응할 수 없기 때문에 발생하였다. 이 문제를 해결하기 위해 다양한 경우에 대해 유동해석을 통해 accumulator 설치와 각 단의 충전모드 전환 순서를 적절히 조정함으로써 안정적으로 공급할 수 있음을 확인하였다.