• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.4
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• pp.300-309
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• 2017

A spacecraft obtains a reaction momentum required for an orbit correction and an attitude control by exhausting a combustion gas through a small thruster in space. If the exhaust plume collides with spacecraft surfaces, it is very important to predict the exhaust plume behavior of the thruster when designing a satellite, because a generated disturbance force/torque, a heat load and a surface contamination can yield a life shortening and a reduction of the spacecraft function. The purpose of the present study is to ensure the core technology required for the spacecraft design by analyzing numerically the exhaust gas behavior of the 10 N class bipropellant thruster for an attitude control of the spacecraft. To do this, calculation results of chemical equilibrium reaction between a MMH for fuel and a NTO for oxidizer, and continuum region of the nozzle inside are implemented as inlet conditions of the DSMC method for the exhaust plume analysis. From these results, it is possible to predict a nonequilibrium expansion such as a species separation and a backflow in the vicinity of the bipropellant thruster nozzle.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.5
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• pp.1-9
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• 2021

As part of the commercialization research of small gas turbine engines, starting and normal operation control logic research of small gas turbine engine was conducted. It was investigated how the igniter, starting motor and fuel pump/valve are controlled during the ignition and normal operation process and it was applied to the prototype engine control unit(ECU) of the small gas turbine engine for commercialization research. Based on the ground test results, an ECU for flight test is being developed, and after completion of the development, an altitude test will be performed through an altitude test facility of Korea Aerospace Research Institute.

• The Magazine of the Society of Air-Conditioning and Refrigerating Engineers of Korea
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• v.36 no.12
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• pp.27-33
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• 2007

• Proceedings of the KAIS Fall Conference
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• 2010.05b
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• pp.1000-1003
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• 2010

기존 Non-Road 가솔린 불꽃점화 소형엔진의 경우 대부분이 캬브레이터 연료 공급 방식으로 연비 및 배기가스 성분이 매우 열악한 실정이다. 본 연구에서는 이러한 단점을 극복하고 배기규제에 대응하기위하여 전자제어식 연료분사방식으로 엔진을 변경하고, 관련핵심 부품의 설계 및 개발을 수행하였다. 전자제어식 소형엔진에 적합한 인젝터, 연료펌프를 선정하였으며 연료레일은 새로이 설계하여 장착하였다. 최적의 인젝터, 연료펌프 및 흡기포트를 선정하기위해 각각의 핵심 부품에 대한 성능개발을 수행하였다. 제작된 소형엔진은 엔진성능 개발을 통하여 연비 및 배기가스를 개발할 예정이다.

• Journal of the korean Society of Automotive Engineers
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• v.15 no.3
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• pp.19-31
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• 1993

디젤자동차는 가솔린 자동차에 비하여 연료소비효율(fuel economy)이 20-30% 정도 높고 고출력을 낼수 있어 이의 수요가 증가하고 있다. 본 고에서는 디젤자동차에서 배출되는 수많은 화학물질중에서 문제가 되고 있는 입자상물질, NOx 및 SO$_{2}$를 제거하는 기술에 대하여 살펴본다. 이러한 오염물질의 저감을 위하여는 배기가스 재순환, 분사시기의 조절, 인터쿨링 같은 연소기술의 개선과 유황분이 적고, 방향족화합물의 함량이 적은 청정연료를 사용하여 어느 수준까지는 목적을 달성할 수 있다. 1. 디젤자동차 배출허용기준. 2. 배기가스 정화기술. 2.1 트랩기술(trap technology). 2.2 재생기술(regeneration technology). 2.3 제어 및 센서기술(control and sensor technology)

• Journal of the Korea Academia-Industrial cooperation Society
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• v.14 no.5
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• pp.2069-2074
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• 2013

The use of the electromagnetic clutch water pump for internal combustion engine vehicles saves fuel and leads to a reduction in emissions. The clutch water pump allows the engine cooling system to select the optimum operation condition by using coolant flow rate on/off control. This study investigated the characteristics of fuel consumption and emissions of the diesel engine cooling system using the clutch water pump. The electromagnetic clutch operation reduced by about 49% of engine warm up period at idle condition and controlled the optimum high coolant temperature at driving condition. Therefore, fuel consumption was enhanced by about 5%, and emissions such as HC, CO and $CO_2$ were also reduced to a certain degree even though NOx increased a little bit, compared to those of the conventional water pump under NEDC mode which represents the real driving pattern.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.9
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• pp.799-804
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• 2015

The purpose of this study is to analyse the dynamic disturbances(disturbed forces and disturbed torques) due to attitude control thruster's plume impingement on the solar arrays. To produce database of the dynamic disturbances a sweep analysis was done, in which the two parameters are used; the distance between the thruster and solar arrays and the thruster tilt angle. Based on the database, a third order polynomial approximation is computed to represent the characteristics of the disturbed forces and torques. The final results are the coefficients of the approximation for each solar array angle position. These results as input data are used to optimize the configuration of the attitude control thrusters. This analysis is appled to the two candidate solar arrays for Geo-Kompsat-2 satellite and the results of the disturbed forces and disturbed torques are compared and analysed.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.6
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• pp.1147-1155
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• 1989

본 연구에서는 정상모우드 운전조건에서 $O_{2}$ 센서의 단점을 극복할 수 있고 모델링 오차나 외란에 대하여 강인한 슬라이딩 모우드 제어방법을 적용하여 새로운 열료분사 제어기를 설계하고자 한다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.16 no.8
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• pp.5541-5549
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• 2015

This paper introduces a safer and more power efficient heater by using induction heating, to apply to the semiconductor wafer fabrication exhaust gas cleaning system. The exhaust gas cleaning system is currently made with filament heater that generates an endothermic reaction of N2 gas for the removal of moisture. Induction theory, through the bases of theoretical optimization and electronic implementation, is applied in the design of the induction heater specifically for the semiconductor wafer exhaust system. The new induction heating design provides a solution to the issues with the current energy inefficient, unreliable, and unsafe design. A robust and calibrated design of the induction heater is used to optimize the energy consumption. Optimization is based on the calibrated ZVS induction circuit design specified by the resonant frequency of the exhaust pipe. The fail-safe energy limiter embedded in the system uses a voltage regulator through the feedback of the MOSFET control, which allows the system performance to operate within the specification of the N2 Heater unit. A specification and performance comparison from current conventional filament heater is made with the calibrated induction heater design for numerical analysis and the proof of a better design.

• Journal of Aerospace System Engineering
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• v.12 no.5
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• pp.8-15
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• 2018

The geostationary satellite uses a liquid apogee engine, to obtain a required velocity increment to enter a geostationary orbit. However, as the liquid apogee engine operates in the vacuum, a considerable disbursement of exhaust plume flow, from the liquid apogee engine can trigger a backflow. As this backflow may possibly collide with the satellite directly, it can cause adverse effects such as surface contamination, thermal load, and altitude disturbance, that can generate performance reduction of the geostationary satellite. So, this study investigated exhaust plume behavior of 400 N grade liquid apogee engine numerically. To analyze exhaust plume behavior in vacuum condition, the DSMC (Direct Simulation Monte Carlo) method based on Boltzmann equation is used. As a result, thermal fluid characteristics of exhaust plume such as temperature and number density, are observed.