• 한국자동차공학회논문집
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• 제11권5호
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• pp.163-169
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• 2003

Modeling of engine-generator system and its control responses are investigated using high performance generator controller. The nonlinear engine is modeled using mean torque production model based on experimental engine map. In case of diesel engine. the amount of injected fief is decided by engine controller depending on the APS(Acceleration Position Sensor) value. An electromechanical generator model contains electrical circuits and moment of inertia. The generator controller maximizes the performance of generator using decoupling and linearized current feedback control. The generator control system consists of 3-phase IGBT inverter and controller board based on 32 bit floating point DSP. Field oriented control algorithm with digital current feedback control at 10kHz sampling enabled high performance torque and speed control of induction machine. Not only the steady state but also the transient state responses can be evaluated through a batch test of the engine generator system. Developed engine and generator modeling and control can be utilized in various applications such as Series Hybrid Electric Vehicle(SHEV), engine-generator for emergency, and other hybrid generation systems.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
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• pp.219-222
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• 2003

Turbo generator system need starter for gas turbine engine. Turbo generator has high rate gearbox for reduce rotating speed. Because a conventional generator could not operate same speed of gas turbine engine. But Recently turbo generator system is directly connected a gas turbine engine with a super high-speed generator. In this paper, starter driver are implemented direct coupled turbo generator system, Which is directly connected 100kW, 60,000rpm gas turbine engine and 25kW 60,000rpm super high speed generator.

• International Journal of Aerospace System Engineering
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• 제5권2호
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• pp.16-22
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• 2018

An analysis has been made on the performance variation due to pressure drop change at propellant supply pipes of liquid rocket engine. The objective is to compare the effectiveness of control variables to tune the liquid rocket engine performance. The mode analysis program has been used to estimate the engine performance for different modes which is realized by controlling the flow rate of propellant. The oxidizer of combustion chamber, the fuel of combustion chamber, the oxidizer of gas generator and the fuel of gas generator are the independent variables to control engine thrust, engine mixture ratio and temperature of gas generator product gas. The analysis program is validated by comparing with the powerpack test results. The error range of compared variables is order of 4%. After comparison of tuning effectiveness it is turned out that the pressure drop at oxidizer pipe of gas generator and pressure drop at combustion chamber fuel pipe and the pressure drop at the fuel pipe of gas generator can effectively tune the thrust of engine, mixture ratio of engine and temperature of product gas from gas generator respectively.

• 전기학회논문지
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• 제57권6호
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• pp.966-971
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• 2008

Free-piston engine system is a new type energy converter which uses a linear motion of piston by using linear generator. In free-piston engine system, the piston is not connected to a crank-shaft. The major advantages of free-piston engine system are high efficiency and low mechanical loss from the absence of motion conversion devices. Linear generator of free-piston engine system is used as generator and starting motor. In design step, considering of back-emf and detent force characteristics for generating mode and thrust and control characteristics for starting mode is needed. In this research, generating mode of flat-type linear generator and tubular-type linear generator is analyzed by finite element analysis method and starting mode of both type linear generators is analyzed by using capability curve. Capability curve is plotted from electrical parameters of both type linear generator and motion profile is calculated from mechanical parameters.

• International Journal of Aerospace System Engineering
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• 제6권2호
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• pp.11-16
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• 2019

A system analysis program has been developed for a gas generator cycle liquid rocket engine of 30 ton class. Numerical models have been proposed for a combustor, a turbopump, a gas generator and pressure drop through a regenerative cooling system. Numerical algorithm has been validated by comparing with the published data of MC-1. The major source of error is not the numerical algorithm but the imperfect performance models of subsystems. So the precision of the program can be improved by revising the performance models using experimental data. The sea level specific impulse and vacuum specific impulse have been demonstrated for a 30 ton class gas generator engine. The optimal condition of combustor pressure and mixture ratio for specific impulse which is a typical characteristic of a gas generator cycle engine has been illustrated.

• 한국조명전기설비학회:학술대회논문집
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• 한국조명전기설비학회 2006년도 춘계학술대회 논문집
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• pp.395-398
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• 2006

this paper provides a novel method to start the linear engine coupled linear generator from dead stop to its final steady state operation. This method depends mainly to use the linear generator mounted on the shaft of the linear engine to provide the required thrust force to move and oscillate the linear engine from bottom to top dead centers. It is a cost effective approach to start the internal linear combustion engine using its coupled tubular permanent magnet linear generator proposed here. This linear generator operates in this case in motoring mode, providing the required thrust force by feeding this linear generator phases with currents by using a three phase PWM inverter controlled by position feedback scheme. In order to provide the desired thrust force with specific value and direction, a position feedback is required to control the free piston engine motion through controlling the inverter switches using PWM control scheme.

• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2016년도 추계학술대회
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• pp.297-299
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• 2016

본 논문에서는 MATLAB/SIMULINK 기반의 LNG 선박용 Power Generator 모델링을 수행하고 시뮬레이션 결과 모니터링이 가능한 인터페이스를 구현하였다. Power Generator의 주요 구성은 기계적 동력을 공급하는 엔진부(Diesel 엔진, Turbine 엔진)와 기계적 동력을 받아 전력을 생산 및 공급을 하는 동기발전기가 있다. 또한, 단일 용량을 초과하는 전체 부하를 공유하기 위해 병렬 연결된 Generator의 Load Sharing과 선박의 가상 부하에 따른 시뮬레이션을 수행하였다. 시뮬레이션 결과와 가상 부하에 따른 예상 결과의 비교를 통해 Power Generator 모델링의 신뢰성을 검증하였다.

• 한국추진공학회지
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• 제25권1호
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• pp.68-76
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• 2021

본 연구에서 대상으로 삼은 직렬 하이브리드 시스템은 무인기용으로 왕복엔진, 발전기, 배터리를 주 동력원으로 사용한다. 발전기는 왕복엔진의 구동축에 직결되며, 왕복엔진-발전기 세트의 운용 특성은 지상통합시험을 통해 확인하였다. 본 연구에서는 해당 시험 결과를 바탕으로 왕복엔진-발전기 출력과 배터리 출력을 효율적으로 사용하기 위한 제어로직을 제시하였고, 로직에 따른 왕복엔진-발전기와 배터리의 출력 변동은 시뮬레이션을 통해 확인하였다. 그 결과, 발전기 출력은 제시된 제어로직에 의해 배터리 출력과 함께 추진요구전력을 공급함을 확인하였다.

• 한국군사과학기술학회지
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• 제25권5호
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• pp.539-544
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• 2022

This research shows the test performance of a 6 kW-scale hybrid electric power system for the high endurance drone. The power system is composed of a two-stroke reciprocal engine, starter-generator and battery, and they are integrated as one power unit. The engine is designed to provide the house for holding the starter-generator at the end of a crankshaft in turn the engine and starter-generator can maintain the same speed during the operational period. In this way, the generated power is readily controlled by just manipulating an engine throttle movement. Moreover, the starter-generator can initiate an engine operation with an aid of battery power until the combustion process becomes stabilized. In consequence, integration mechanism between an engine and generator is simplified, which results in weight reduction achieved. The duty of back-up battery is to provide a starting power to generator via a system controller in addition to covering momentarily power shortage. Therefore, the electric power system is vindicated to provide 6 kW power through a ground test.

• 대한기계학회논문집B
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• 제34권5호
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• pp.563-568
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• 2010

30톤급 액체산소/케로신 액체로켓엔진개발의 중간단계로 터보펌프-가스발생기 개회로 연계시험이 수행되었다. 터보펌프-가스발생기 개회로 연계시험은 엔진시스템 작동 모사 환경 시험으로서 가스발생기로의 추진제는 터보펌프 출구를 통해 공급되지만, 가스발생기 출구 가스는 터빈 구동에 이용되지 않고 외부로 배출된다. 터보펌프-가스발생기 개회로 연계시험 목적, 시험설비 구성, 제어시스템의 작동 조건, 시험 수행 절차, 연계시험기의 구성 형태, 개회로 연계시험 결과가 제시되었다. 터보펌프-가스발생기 개회로 연계시험 결과, 연계시험기의 예냉 절차와 시동 특성, 정격 작동성 및 안정적인 종료 특성이 액체로켓 엔진시스템 작동 환경 모사 조건에서 확인되었다.