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화학수소화합물을 이용한 소형 무인항공기용 연료전지 시스템 연구 - II. 경량 연료전지 추진 시스템

Fuel cell system for SUAV using chemical hydride - II. Lightweight fuel cell propulsion system

  • Hong, Ji-Seok (Korea Aerospace University, School of Aerospace and Mechanical Engineering) ;
  • Park, Jin-Gu (Korea Aerospace University, School of Aerospace and Mechanical Engineering) ;
  • Sung, Myeong-Hun (Korea Aerospace University, School of Aerospace and Mechanical Engineering) ;
  • Jeon, Chang-Soo (Korea Aerospace University, School of Aerospace and Mechanical Engineering) ;
  • Sung, Hong-Gye (Korea Aerospace University, School of Aerospace and Mechanical Engineering) ;
  • Shin, Seock-Jae (Korea Institute of Science and Technology, Fuel Cell Center) ;
  • Nam, Suk-Woo (Korea Institute of Science and Technology, Fuel Cell Center)
  • 투고 : 2012.09.29
  • 심사 : 2013.02.26
  • 발행 : 2013.03.01

초록

화학수소화합물 수소저장방법을 이용한 100 W 급 연료전지 시스템을 소형 무인항공기의 추진시스템으로 적용하는 연구를 수행하였다. 소형/경량 수소 발생 제어장치와 연료전지/배터리 하이브리드 전력 공급 방법으로 효율성 및 안정성을 증대하였다. $NaBH_4$ 수용액을 이용한 수소 발생장치와 Dead-end 형식의 PEMFC를 이용한 연료전지 시스템의 지상, 비행 시험이 수행되었다. 연료전지 스택을 안정적으로 운전하고, 높은 효율을 얻기 위해 45 kPa의 압력을 가하는 방법을 적용하였다. 수소 발생 시스템 내부 압력을 이용한 수소 발생 제어 장치는 45~55 kPa 사이에서 유지되며 안정적으로 수소가 공급되는 것을 확인하였다. 그 결과, 100 W 연료전지 시스템이 소형 무인항공기 적용하기에 무게 및 소비 전력을 만족함을 확인하였고, 시험비행을 통해 성능을 입증하였다.

A 100 W fuel cell system using chemical storage method has been applied for a propulsion system of the SUAV(Small Unmanned Aerial Vehicle). A fuel cell and battery have been combined for both the small/light hydrogen generation control system and the hybrid power supply system. A small hydrogen generation device was implemented to utilize NaBH4 aqueous solution and dead-end type PEMFC system, which were evaluated on the ground and by the flight tests. The system pressurized at a 45kpa stably operates and get higher fuel efficiency. The pressure inside of the hydrogen generation control system was maintained at between 45 kPa and 55 kPa. The 100W fuel cell system satisfies the required weight and power consumption rate as well as the propulsion system, and the fuel cell system performance was demonstrated through flight test.

키워드

참고문헌

  1. Rocheleau, Richard E. "Final Technical Report: Fuel Cell Stack Testing and Durability in Support of Ion Tiger UAV", OMB No.0704-0188
  2. Keun-Bae Kim, "Technical Trends for Fuel Cell Aircraft", Current Industrial and Technological Trends in Aerospace, Vol 7, Issue 2, 2009, pp. 85-105
  3. AeroVironment's unmanned aircraft achieves record flight. Fuel Cell Bull 8, 2007
  4. S.U. Jeong, R.K. Kim, E.A. Cho. H.-J. Kim, S.-W. Nam, I.-H. Oh, S.-A. Hong, S.H. Kim, "A Study on hydrogen generation from $NaBH_4$ solution using the high performance Co-B catalyst", Journal of Power Souces, Vol. 144, Issue 1, 1 June. 2005, pp.129-134 https://doi.org/10.1016/j.jpowsour.2004.12.046
  5. Myeong-whun Seung, Ji-Seok Hong, Dong-Hyun Kim, Hee-Man Kim, Bo-Young Lee, Hong-Gye Sung, "Fuel Cell propulsion system utilizing hydrogen generating device and preflight test of the UAV(I)", The Society for Aerospace System Engineering, 2008 SASE Fall Conference, 2008
  6. Ji-seok Hong, Jin-Gu Park, Hong-Gye Sung, Seock-Jae Shin, Suk-Woo Nam, "Hydrogen generation control of PEMFC propulsion system for UAV," Asia-Pacific International Symposium on Aerospace Technology, 2010

피인용 문헌

  1. Performance Evaluation of Hydrogen Generation System using NaBH4 Hydrolysis for 200 W Fuel Cell Powered UAV vol.43, pp.4, 2015, https://doi.org/10.5139/JKSAS.2015.43.4.296