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元聖弘(Sunghong Won),任承彬(Seoungbin Lim),裵在男(Jaenam Bae),金明鎭(Myungchin Kim),李柱(Ju Lee) 대한전기학회 2006 전기학회논문지 B Vol.55 No.12
As one of numerical methods, the Finite Element Method (FEM) is very widely used to analyze electrical machines these days. However, the most electrical machines have a motion and it is very important to consider a motion in electrical machine analysis. In this paper, Moving Surface Method is suggested as a new approach to consider a motion and discuss its advantages and disadvantages. And also, a finite element analysis program which applied Moving Surface Method is developed and we evaluate its results compared with experimental results of a real model.
저심도철도용 선형유도전동기의 공극 불균일 과도특성 분석 연구
이형우(Hyung-Woo Lee),박찬배(Chan-Bae Park),원성홍(Sunghong Won) 대한전기학회 2013 전기학회논문지 Vol.62 No.5
This paper presents an parallel type Linear Induction Motor with ununiform airgap for a shallow-depth underground train with 100‰ grade and 15 m curvature. This parallel type LIM has enough gradability but has inherently ununiform airgap between center and end parts. Consequently, performance when the train passes curved section should be considered with transient analysis. Moreover, general parallel operation, 1C2M which is usually used for train operation, deteriorates LIM performance because of different line velocity between inner and outer LIMs. Transient analysis has many problems such as huge model, lots of meshes, very long calculation time, truncation error and so on. This paper has presented a novel technique using equivalent linear rotating model in order to solve these problems and has analyzed parallel type LIM by using the proposed technique. Finally, LIM performance according to independent operating control has been investigated.
고정익 수직이착륙 무인항공기를 위한 하이브리드-전기 추진시스템의 타당성 연구
김보성(Boseong Kim),박정규(Jeonggyu Bak),윤승현(Senghyun Yun),조수영(Sooyoung Cho),하주형(Juhyung Ha),박규성(Gyusung Park),이근호(Geunho Lee),원성홍(Sunghong Won),문창모(Changmo Moon),조진수(Jinsoo Cho) 한국항공우주학회 2015 韓國航空宇宙學會誌 Vol.43 No.12
일반적인 수직이착륙 항공기는 높은 출력대 중량비의 가스터빈엔진을 사용한다. 그러나 높은 연료 소모율로 인해 소형 항공기에는 적합하지 않다. 본 연구에서는 직렬 하이브리드-전기 추진시스템을 대안으로 제안하였으며, 시스템을 구성할 소형엔진과 전기모터, 배터리에 대한 기술조사·비교분석을 수행하였다. 연구를 위한 고정익 수직이착륙 무인항공기로 I社의 65 kg급 수직이착륙 P-무인기를 사용하였다. 개발한 발전제어 및 전력제어 알고리즘의 타당성과 항속시간을 예측하기 위해 Matlab/Simulink®를 이용한 시뮬레이션을 수행하였다. 그 결과 알고리즘이 비교적 잘 작동하는 것을 확인하였고, 직렬 하이브리드-전기 시스템이 임무형상을 만족하는 7 시간의 항속시간을 충분히 만족 할 수 있을 것으로 예측하였다. General VTOL aircraft uses gas turbine engine which has high power to weight ratio. However, in the VTOL UAV in small sector, the gas turbine as a prime mover is not adequate because of the limitation of the high fuel consumption ratio of the gas turbine. In this research, The Series Hybrid-Electric Propulsion System(SHEPS) has been proposed and technology survey & comparison analysis has conducted to constitute propulsion system for engine, electric motor and battery. To achieve this object a 65kg-class P-UAV from “Company I” was used. And to estimate the validity of power control algorithm and developed power management control, Matlab/simulink<SUP>®</SUP> has been used for the simulation. As a result, the developed algorithm worked comparatively well and the research has predicted that SHEPS was satisfied enough for 7 hour of endurance for mission profile.