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대체에너지를 사용한 글라이더형 고고도 장기체공 무인항공기의 초기사이징

Initial Sizing of a Glider Type High Altitude Long Endurance Unmanned Aerial Vehicle Using Alternative Energy

  • Han, Hye-Sun (Department of Aerospace Engineering, Graduate School, Sejong University) ;
  • Kim, Chan-Eol (Department of Aerospace Engineering, Graduate School, Sejong University) ;
  • Hwang, Ho-Yon (Department of Aerospace Engineering, Sejong University)
  • 투고 : 2013.08.15
  • 심사 : 2013.12.23
  • 발행 : 2014.01.01

초록

본 연구에서는 대체에너지로 태양광과 수소재생연료전지를 사용하는 고고도 장기체공 무인기의 초기 사이징을 수행하였다. 박스 윙 형태의 형상 대신 해외에서 연구가 많이 진행되어 상대적으로 기본 자료들이 풍부한 글라이더 형태의 형상을 선택하였다. 이륙중량 150 kg 급으로 추진 시스템은 모터와 프로펠러, 태양광 전지, 전기분해를 통해 재충전이 가능한 액체수소 연료전지로 구성되어있다. 하루 동안 순항 비행 시 필요한 최소 요구 에너지와 낮 시간으로부터 얻을 수 있는 태양광 에너지와의 에너지 균형을 고려하여 가로세로비, 날개 길이, 면적 등 항공기 설계변수를 변화시키면서 전체 이륙중량을 추정하였다.

In this research, the initial sizing of a HALE(High Altitude Long Endurance) UAV which uses solar power and hydrogen fuel cell as an alternative energy was performed. Instead of a wing box type, a glider type was chosen since it is relatively easy to get a data thanks to many researches abroad. Maximum takeoff weight is around 150Kg and the propulsion system is composed of motor, propeller, solar cell, and hydrogen fuel cell which can be recharged through electrolysis. Maximum takeoff weight was estimated as aspect ratio, wing span, wing area change while considering energy balance of required energy which is necessary for flight during the entire day and available energy which can be taken from the solar cell.

키워드

참고문헌

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피인용 문헌

  1. Initial Climb Mission Analysis of a Solar HALE UAV vol.42, pp.6, 2014, https://doi.org/10.5139/JKSAS.2014.42.6.468