• Title/Summary/Keyword: Propulsion motor

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The research to improve Thrust and Levitation Force characteristic of Linear Synchronous Motor for High-speed Maglev train (초고속 자기부상열차용 선형 동기 전동기의 추력 및 부상력 특성 개선을 위한 연구)

  • Hong, Hyun-Seok;Oh, Se-Young;Han, Jung-Ho;Lee, Ju
    • Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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    • v.28 no.6
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    • pp.75-84
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    • 2014
  • A linear synchronous motor (Linear Synchronous Motor, under LSM) is suitable for Maglev train. This is 500km/h or more for running high-speed propulsion system of high-efficiency, high-output characteristics. Also, as high-speed running, it is needed solution to reduce output ripple component cause bad riding like noise and vibration. So this paper was designed 500km/h-class Maglev train and analyzed characteristics of the LSM base model using finite element analysis method. Further, improved model is designed to improve characteristics of thrust and levitation force by enforcing design parameters analysis and sensitivity analysis. And it was applied skew on field in order to reduce the ripple component still remaining. Skew interpretation of the two-dimensional is proposed and this is verified by carrying out three-dimensional finite element analysis comparing two values. It proved to be valid of skew of the two-dimensional analysis.

Comparison of Battery Charging Strategies for PHEVs using Propulsion Motor Inductance and Multi-Function Inverter (인덕터 및 모터 인덕턴스를 이용한 PHEV 배터리 충전 기법 비교 분석)

  • Woo, Dong-Gyun;Choe, Gyu-Yeong;Kim, Jong-Soo;Lee, Byoung-Kuk;Kang, Gu-Bae
    • The Transactions of the Korean Institute of Power Electronics
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    • v.16 no.4
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    • pp.326-333
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    • 2011
  • This paper studies battery charging methods using existing motor inductance and 3-phase inverters without an additional charger to charge the battery of Plug-in Hybrid Electric Vehicles (PHEVs). As inverter switch control and motor coil used as the energy storage device for boosting make the system the boost converter, the additional charger is eliminated and volume, weight, and cost for the charger are reduced. Various charging methods according to topologies of the system and configurations of the controller are analyzed and verified by PSIM simulation.

Microcracking of Motor Case with Fiberite 934/T300 Laminates under fatigue Loads (피로하중을 받는 Fiberite 934/T300 복합재료로 만들어진 연소관의 미세균열 연구)

  • 김형원;김성은
    • Journal of the Korean Society of Propulsion Engineers
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    • v.1 no.1
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    • pp.82-88
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    • 1997
  • The goal is to assess the effect of fatigue loading on mechanical properties of Fiberite 934/T300 laminates of pressure vessel using the recent variational mechanics analysis. This analysis has been useful in providing fracture mechanics interpretation of matrix microcracking in cross-ply laminates. This paper describes using the new energy release rate analysis for a fracture mechanics based interpretation of microcrack formation during fatigue loading. The master plot by modified Paris-law gives a complete characterization of a material system's resistance to microcrack formation.

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KM 추진제 개발 (I)

  • 최성한;박의용;조인현
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2000.04a
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    • pp.26-26
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    • 2000
  • KM(Kick Motor)는 항우연에서 주관하여 개발하고 있는 3단형 과학관측로켓(KSR-III)이다. 본 연구는 이 KM에 적용되는 추진제 개발로서 추진기관에서 요구하는 성능, 밀도, 연소특성, 기계적특성, 점화성, 추진제/라이너/EFDM 접착력을 달성하고, 장기저장시 추진제에 작용하는 온도, 중력등 하중에 대한 추진제의 내구성을 확인하는 수면예측시험을 통해 KM이 사용하는 기간중 요구성능을 발휘할 수 있는 추진제 개발을 목표로 하고 있다. 본 논문에서는 KM 추진제 개발중 1차적으로 추진기관 요구성능을 달성하기 위해서 추진제 성능분석을 통한 기본조성을 설정하고, 이 기간조성을 토대로 밀도, 연소특성, 기계적 특성, 추진제/라이너/EPDM 접착력 실험 결과등을 정리하였고, 추진제 성능을 확인하는데 일반적으로 널리 이용하는 있는 표준모타(ST-8)에 적용하여 이론적 성능분석 및 실제 연소시험을 실시하여 그 결과를 비교 분석하였다.

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Development of Stabilizing Agent for Double Base Propellant Rocket Motor (복기 추진제 로켓 모타 연소 안정제 개발)

  • 손원경;최성한;이원복
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1994.04a
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    • pp.23-26
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    • 1994
  • 130mm D.B. 추진기관의 고온 시험에서 나타난 극심한 이상 연소 현상을 해결하기 위해 미세한 고체 입자들을 연소 가스에 분산시켜 불안정 연소를 억제하는 particulate damping 효과를 연구하였다. 고체 입자로서 효과적인 것으로 알려진 $K_2$$SO_4$. ZrC, Graphite를 CTPB, HTPB 고분자 물질에 충진시켜 epoxide, isocyanate 반응기와 가교 반응을 일으킴으로써 고무상의 탄성체 성질을 갖게 하는 $K_2$$SO_4$/CTPB, ZrC/Graphite/HTPB, ZrC/Graphite/AP/HTPB, ZrC/AP/HTPB 조성의 연소 안정제를 개발하였다. 이 연소 안정제는 외경 17mm, 길이 1000mm의 안정봉 형태로 제작하여 모타의 중심 cavity에 조립한 후 지상 연소 시험을 통하여 성능을 확인하였다. 시험 결과, 조성에 AP를 포함시켜 연소 안정제에 일정한 연소 속도를 부여하여 추진제 grain 연소 동안 고체 입자를 연소 가스에 분산되게 설계한 ZrC/Graphite/AP/HTPB, ZrC/AP/HTPB 조성의 연소 안정제가 불안정 연소 억제에 효과적인 것으로 나타났다.

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Status of Advanced Tecnhologies and Domestic Researches for Development of Korean Next Generation Maglev (한국형 차세대 자기부상열차 개발을 위한 선진기술분석 및 국내연구현황)

  • Cho, Han-Wook;Bang, Je-Sung;Han, Hyung-Seok;Sung, Ho-Kyung;Kim, Dong-Sung;Kim, Byung-Hyun
    • The Transactions of The Korean Institute of Electrical Engineers
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    • v.57 no.10
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    • pp.1767-1776
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    • 2008
  • This paper presents the status of advanced technologies and domestic researches for development of Korean next generation maglev. Generally, two specific configurations such as the EMS (Electromagnetic Suspension) with LSM (Linear Synchronous Motor) and EDS (Electrodynamic Suspension) with LSM can be employed as a propulsion and levitation device of high-speed maglev. Worldwide high-speed maglev developments refer to projects such as the German Transrapid with EMS, the Japanese MLX with EDS, and the U.S. Inductrack with PM (Permanent Magnet) EDS maglev system. In this paper, the propulsion and levitation systems of these world wide high-speed maglev have been reviewed and analysed.

Analysis on Roll Damping Induced by Propulsion Jet of Rolling Airframe Missile (회전 유도탄의 추진 제트에 의한 롤 댐핑 해석)

  • Jung, Suk-Young;Yoon, Sung-Joon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.6
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    • pp.81-86
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    • 2004
  • Between rolling airframe missile and swirling propulsion jet passing through convergent-divergent nozzle of the rocket motor, occur exchanges of angular momentum which result in the increase of roll speed of the missile. This phenomena in called jet roll damping. In the study jet roll damping was formulated from conservation equation of angular momentum. And the maximum value of the jet roll damping of KPSAM was estimated with assumed swirl velocity distribution at nozzle exit and compared with result of computation of axisymmetric compressible turbulent nozzle flow.

Research of the Improvement of Solid Fuel Regression Rate in Swirl Hybrid Rocket (선회류 하이브리드 로켓에서 고체 연료 후퇴율 향상에 대한 연구)

  • Park Jong-Won;Lee Choong-Won;Ku Kun-Woo;Yoon Myung-Won
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.05a
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    • pp.233-238
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    • 2006
  • Hybrid rocket had many advantage with compared to solid and liquid rockets. In this study, swirl flow hybrid motor was designed and manufactured. And the methods of regression rate improvement were considered. Thrust was calculated with pressure of the combustion chamber and the regression rate was measured by using ultrasonic sensor technique in entire firing conditions. In this study, PMMA fuel and HTPB solid fuel were used in firing test.

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Analysis of absorption and scattering characteristics of alumina particles using Mie theory (Mie Theory를 이용한 알루미나 입자의 흡수 및 산란 특성 분석)

  • Ko, Ju-Yong;Kim, In-Sun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.962-967
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    • 2011
  • Radiative properties of alumina particles which is the main element of the plume from booster and kick motor used for increasing thrust and insertion into the orbit is analyzed. In order to derive the wavelength integrated (i.e., gray) emissivity, emission term in radiative transfer equation is rearranged to be able to tie up with the parameters induced from fundamental particle scattering Mie theory. Result shows that derived gray emissivity with optical properties increases with temperature rising.

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A Study on the Characteristics of Hydro-reactive Metal Fuel Solid Propellants (수반응 금속연료 고체추진제의 특성연구)

  • Kim, Jun-Hyung;Seo, Tae-Seok;Jung, Jung-Yong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.429-431
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    • 2011
  • The characteristics of hydro-reactive metal fuel(HRF) propellant on motor performances such as specific impulse and chamber temperature were analyzed by thermodynamic calculation methods. The thermal analysis and burning rate experiments of HRF propellants were also carried out for studying effects of metal fuels on combustion properties.

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