한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제43권12호
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  • Pages.1097-1107
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  • 2015
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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고정익 수직이착륙 무인항공기를 위한 하이브리드-전기 추진시스템의 타당성 연구

Feasibility Study of a Series Hybrid-Electric Propulsion System for a Fixed Wing VTOL Unmanned Aerial Vehicle

  • Kim, Boseong (Department of Mechanical Engineering, Hanyang University) ;
  • Bak, Jeonggyu (Department of Mechanical Engineering, Hanyang University) ;
  • Yun, Senghyun (Department of Mechanical Engineering, Hanyang University) ;
  • Cho, Sooyoung (Department of Electrical Engineering, Hanyang University) ;
  • Ha, Juhyung (Graduate School of Automotive Engineering, Kookmin University) ;
  • Park, Gyusung (Graduate School of Automotive Engineering, Kookmin University) ;
  • Lee, Geunho (Graduate School of Automotive Engineering, Kookmin University) ;
  • Won, Sunghong (Department of Electrical System, Dongyang-Mirae University) ;
  • Moon, Changmo (Aerospace Business Development Division, Hankuk Carbon Co., LTD.) ;
  • Cho, Jinsoo (Department of Mechanical Engineering, Hanyang University)
  • 투고 : 2015.08.07
  • 심사 : 2015.11.18
  • 발행 : 2015.12.01
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초록

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 I사(社)의 65 kg급 수직이착륙 P-무인기를 사용하였다. 개발한 발전제어 및 전력제어 알고리즘의 타당성과 항속시간을 예측하기 위해 Matlab/simulink$^{(R)}$를 이용한 시뮬레이션을 수행하였다. 그 결과 알고리즘이 비교적 잘 작동하는 것을 확인하였고, 직렬 하이브리드-전기 시스템이 임무형상을 만족하는 7시간의 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$^{(R)}$ 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.

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