• Title, Summary, Keyword: Propulsion control device

Search Result 71, Processing Time 0.043 seconds

A Study on Propulsion Control Device Characteristics of Small-scale Electric Railway Vehicle according to Driving Curve Tracking using Fuel Cell Generation System (연료전지 발전시스템을 이용한 축소형 철도차량의 운전곡선 추종에 따른 추진제어장치 특성 고찰)

  • Jung, No-Geon;Chang, Sang-Hoon;Kim, Jae-Moon
    • The Transactions of The Korean Institute of Electrical Engineers
    • /
    • v.64 no.12
    • /
    • pp.1804-1809
    • /
    • 2015
  • The study in railway system to apply a fuel cell system with high efficiency and mobility than other renewable energy is being actively conducted. It is needed a analysis on load characteristics and control method of rolling stock in order to apply to rolling stock. This paper presents study on control small-scale prototype power converter electric railway vehicle using fuel cell generation system. Experiment is conducted through real fuel cell generation system and reference speed applying the driving curve of the actual electric railway vehicle was applied. Also, output voltage of boost converter is controlled considering characteristic of fuel cell. And it was confirmed characteristic according to powering and regeneration of inverter.

Development of KSR-III Propulsion Feeding System (KSR-III 추진기관 공급계 개발)

  • 이대성;조인현;정태규;강선일;김용욱;정영석;권오성;정동호;오승협
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.6 no.4
    • /
    • pp.37-45
    • /
    • 2002
  • The development process of KSR-III propulsion feeding system is subscripted. The purpose of propulsion feeding system is to feed a certain amount of propellant from propellant tank to engine by the end of combustion. Pressure-fed liquid rocket, KSR-III has the unique characteristics of both pressure regulator and cavitation venturi as a passive flow control device. Main parameters of feeding system are confirmed by both water test and CFD(전산유체) technique. Flow control effect with venturi is confirmed by water test. Initial stabilization characteristic of pressure regulator is confirmed by real propellant test. And, to avoid the effect of resonance between rocket and feeding system, this article deal with POGO(포고) analysis to the feeding system.

Development of AC Electric Vehicle Propulsion System (Converter/Inverter) using IPM Switching Device (IPM 스위칭 소자를 적용한 AC 전동차 추진제어장치 (Converter/Inverter) 개발)

  • Kno Ae-Sook;Kim Tae-Yun
    • The Transactions of the Korean Institute of Power Electronics
    • /
    • v.10 no.3
    • /
    • pp.233-240
    • /
    • 2005
  • In this paper, AC electric vehicle propulsion system(Converter/Inverter) using high power semiconductor, IPM is proposed. 2-Parallel operation of two PWM converter is adopted for increasing capacity of system and the harmonic content is eliminated by the phase shaft between two PWM converters switching phase. VVVF inverter control is used a mixed control algorithm, where the vector control strategy at low speed region and slip-frequency control strategy at high speed region. The proposed propulsion system is verified by experimental results with a 1,350kW converter and 1,100kVA inverter with four 210kW traction motors.

Development of AC Electric Vehicle Propulsion System (Converter/Inverter) using IPM Switching Device (IPM 스위칭 소자를 적용한 AC 전동차 추진제어장치 (Converter/Inverter) 개발)

  • Kim T. Y.;Kno A. S.;Hwang K. C.;Choi J. M.;Kim J. B.
    • Proceedings of the KIPE Conference
    • /
    • /
    • pp.298-302
    • /
    • 2004
  • In this paper, AC electric vehicle propulsion system(Converter/Inverter) using high power semiconductor, UM(Intelligent Power module) is proposed. 2-Parallel operation of two PWM converter is adopted for increasing capacity of system and the VVVF inverter control is used a mixed control algorithm, where the vector control strategy at low speed region and slip-frequency control strategy at high speed region. The proposed propulsion system is verified by experimental results with a 1,350kW converter and 1,100kVA inverter with four 210kW traction motors.

  • PDF

Preliminary design of lunar lander ground test model (달착륙선 지상 시험 모델을 위한 추진시스템 기본 설계)

  • Kim, Su-Kyum;Yu, Myoung-Jong;Choi, Ji-Yong;Lee, Jae-Won
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • /
    • pp.27-30
    • /
    • 2011
  • For the successful development of korean lunar lander, the ground test is required in order to verify performance of propulsion system, attitude control system, performance of landing device and etc. In order to develop the lunar lander ground test model, development of large size thruster and pressure regulated propulsion system is now in progress. In this paper, the results of 200N class monopropellant thruster development and propulsion system design will be presented.

  • PDF

Propulsion System(Motor-Block) for High-Speed Train using IGCT Device (IGCT 소자를 사용한 고속전철용 추진제어장치(MOTOR-BLOCK))

  • Cho Hyun-Wook;Kim Tae-Yun;Kno Ae-Sook;Jang Kyung-Hyun;Lee Sang-Jun;Choi Jong-Mook
    • Proceedings of the KSR Conference
    • /
    • /
    • pp.665-670
    • /
    • 2005
  • This paper introduces the propulsion system(Motor Block) stabilization test result for Korean High Speed Railway(HSR). The developed propulsion system using high power semiconductor, IGCT(Integrated Gate Commutated Thyristor) consists of two PWM converter and VVVF inverter. In this paper, overall configuration of propulsion system is briefly described and stabilization tests are made to verify the developed propulsion system. The presented test results shows beatless control method of inverter output current at the 200km/h and performance test of BCH.

  • PDF

Study of Micro Propulsion System Based on Thermal Transpiration (열적발산원리를 이용한 마이크로 추진장치에 대한 연구)

  • Jung, Sung-Chul;Shin, Kang-Chang;Kim, Youn-Ho;Kim, Hye-Hwan;Lee, Yong-Wu;Huh, Hwan-Il
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • /
    • pp.25-29
    • /
    • 2007
  • Minimization of conventional propulsion device has been studied for altitude control of micro satellite. We studied micro nozzle performance and found higher significant loss for a micro nozzle with smaller nozzle throat diameter. To overcome this loss, we proposed thermal transpiration based micro propulsion system. This new system has no moving parts and can control flow by temperature gradient, and this can be an option for potential new micro propulsion system.

  • PDF

Response Characteristic Analysis using Modeling of Propulsion System for 8200 Electric Locomotive (8200호대 전기기관차 추진시스템 모델링을 이용한 응답특성분석)

  • Jung, No-Geon;Chang, Chin-Young;Yun, Cha-Jung;Kim, Jae-Moon
    • The Transactions of The Korean Institute of Electrical Engineers
    • /
    • v.62 no.11
    • /
    • pp.1640-1646
    • /
    • 2013
  • Conventional power conversion unit that is a major part of the propulsion system has applied GTO thyristor as a switching semiconductor device of main circuit since introduction of the 8200 electric locomotive. But problem that quick maintenance is difficult and its cost is increasing occurs because major components of the power conversion unit are slowly discontinued. To solve these, in this paper, it was analyzed the response characteristic of the propulsion system modeling of the 8200 electric locomotive using IGBT which is applied recently to ensure propulsion control technology. As results of response for a Propulsion system modeling, it show that a power conversion unit is controlled by PLL(Phase-locked loop) and SVPWM(Space Voltage PWM) respectively.

The Development of Pressure Regulator of Propellant Tank for KSR-III (KSR-III 추진제 탱크 압력 조절용 레귤레이터 개발)

  • 정영석;조기주;조인현;김용욱;오승협
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.6 no.4
    • /
    • pp.47-58
    • /
    • 2002
  • The pressure regulator has been developed as a pressure-control device of propellant tank in KSR-III. The pressurization system of KSR-III is a basic pressurization system composed of pressurant, He tank and propellant tank. The pressure-control regulator is the most important part of gas-pressurized feed system along with He tank, pyrovalve and He fill valve. The first model of the regulator is tested to satisfy in leakage, strength and basic performance. The second model is tested in the overall test of the KSR-III propulsion system using water. From the test result of the second model, we conclude that the capacity of valve(Cv) must be increased in real system. The third model is modified and tested in the overall test of KSR-III propulsion system using propellant. Finally, the pressure-control regulator is qualified from firing test.

Rupture Prediction of the Rupture Disc Tests using Elastic-Plastic Analysis (탄소성해석을 이용한 파열판의 파열예측)

  • Han, Houk-Seop;Lee, Won-Bok;Koo, Song-Hoe;Lee, Bang-Eop
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • /
    • pp.481-487
    • /
    • 2011
  • This paper provides a comparison between finite element analysis results and test data of rupture disc. Rupture disc is safety device of high pressure equipment. Rupture disc of solid rocket motor is a device to control rupture pressure. Rupture discs were made of AISI 316L. By the elastic-plastic analysis, the stress limit of rupture discs were compared to the test results. The results can be used to control the rupture pressure by the change of the disc size.

  • PDF