• Journal of the Korea Institute of Information and Communication Engineering
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• v.21 no.9
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• pp.1796-1807
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• 2017

The domestic warship propulsion system is at the stage of a hybrid propulsion system changing from a mechanical propulsion system and the propulsion system becomes complicated so it is expected that the function of ECS(Engineering Control System) that controls and monitors the warship propulsion system becomes important. Recently the development of ECS has progressed domestically, so that verification of reliability and stability is required in the process of ECS development. The simulator to be proposed is composed of HILS, it can be divided into a shaft-line dynamics model of the simulating power transmission, a controller model of the simulating the control of the equipment, and a communication model communicating with the ECS. In this paper, we developed simulator for ECS verification for CODLOG hybrid propulsion system, set scenario, and conducted simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1204-1204
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• 2017

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2007.12a
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• pp.63-64
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• 2007

대양 항행하는 거의 모든 선박에서 항해사를 도와 선박의 회두각 유지 및 변침을 목적으로 사용되는 일반적인 오토파일럿 시스템용 대부분 PID형 제어기가 장착되어 있다. 오토파일럿 시스템의 제어상수는 운항 경제성 관점에서 선박의 추진 에너지 손실량(연료소비량)으로써 평가해야 한다. 본 논문에서는 선박 자동 조타 시스템의 정량적인 평가함수를 바탕으로 추진 에너지 손실량이 최소가 되도록 오토파일럿의 제어상수를 구하고자 한다. 이 때 제약조건, 즉 설계사양을 고려한 RCGA를 이용하여 제어상수를 탐색하고, 제안한 방법을 시뮬레이션을 통해 검증한다.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1260-1261
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• 2011

LSM기반의 초고속자기부상열차는 고전압, 대전류의 추진 전력을 공급할 수 있도록 설계되어진 특수한 형태의 추진 인버터와 주행시 부상공극변동에 대해서도 강인한 부상특성을 제공할 수 있도록 개발된 부상제어시스템이 필요하다. 본 논문은 550km/h급 초고속자기부상 시스템에 대한 설계기술의 확보를 위한 것으로, 실 규모시스템 구현에 앞서 축소모형으로 각각의 시스템 구성품을 개발하되 실규도 시스템에 적용하는 방식의 2스텝의 추진용 인버터시스템과 전류원 초퍼기반의 부상시스템 토플로지를 구성하고 그 제어특성의 시험 및 평가를 위해 시뮬레이션을 수행하여 그 가용성을 확인하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.179-182
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• 2011

A practical application of flight-axes/attitude control thrusters to the space launch vehicle and their design development localization are investigated and analyzed. Hydrazine thrusters are mostly used in a final stage of space launch vehicles on account of its higher specific impulse and reliability necessary for the precise attitude control attaining the orbit insertion with higher accuracy.

• Journal of the Korean Institute of Intelligent Systems
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• v.24 no.2
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• pp.129-135
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• 2014

In the paper, we propose a design method for the logistics transportation system using magnetic levitation that has a good characteristics without mechanical friction, noise and dust. The proposed transportation system consists of a levitation control system and a propulsion control system. Magnetic levitation system is an electromagnetic suspension system in which electromagnet generates magnetic attractive force and the attractive force pulls the rail. We design a PID controller for the current control of electromagnets. We use linear induction motors for propulsion of the proposed logistics transportation system and adapt the space vector PWM method for the propulsion control system. The proposed transportation system using magnetic levitation is verified performances through levitation and propulsion experiments.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.4
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• pp.1-11
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• 1999

Thermal behavior of spacecraft propulsion system utilizing monopropellant hydrazine ($N_2$$H_4$) is addressed in this paper. Thermal control performance to prevent propellant freezing in spacecraft-operational orbit was test-verified under simulated on-orbit environment. The on-orbit environment was thermally achieved in space-simulation chamber and by the absorbed-heat flux method that implements an artificial heating through to the spacecraft bus panels enclosing the propulsion system. Test results obtained in terms of temperature history of propulsion components are presented and reduced into duty cycles of the avionics heaters which are dedicated to thermal control of those components. The duty cycles are subsequently converted into the electrical power required in the operational orbit. Additionally, cyclic temperature of each component, which was made under thermal-balanced condition of spacecraft, is compared to the acceptable design range and justified from the viewpoint of system verification.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.51-56
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• 2002

Satellite propulsion system is employed for orbit transfer, orbit correction, and attitude control. The monopropellant feeding system in the low-earth-orbit satellite blowdowns fuel to the thrust chamber. The thrust produced by the thruster depends on fuel amount flowed into the combustion chamber. If the thruster valve be given on-off signal from on-board commander in the satellite, valve will be opened or closed. When the thrusters fire fuel flows through opened thruster valve, instantaneous stoppage of flow in according to valve actuation produces transient pressure due to pressure wave. This paper describes transient pressure predictions of the KOMPSAT-2 propulsion system resulting from latching valve and thrust control valve operations. The time-dependent set of the fluid mass and momentum equations are calculated by MOC.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.79-82
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• 2004

Propellant feeding system is the system to satisfy propellant feeding requirements(mass flow rate, pressure, temperature) at engine inlet of launch vehicle. Propellant feeding test facility is being constructed for the development scheme of pressurization system, processing in tank, propellant piping system, and flow control system that are main technologies in order to develope propellant feeding system. This paper introduces the propellant feeding test facility being constructed in KARI.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.23 no.12
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• pp.136-145
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• 2009

This paper proposes control methods and simulation models of a driving system, which consists of converters and inverters, for high speed trains employing multi-level power converters. The control method of a single phase three-level converter for high-speed trains is designed to use DC values instead of instantaneous current values which are usually used in single-phase application, so that it results in a fast and robust voltage control response. In addition, simulation models of Space Vector Pulse Width Modulation (SVPWM) for single phase three-level converters as well as three level inverters are proposed. Experimental results demonstrate the validity of the simulation model for three-level inverters.