한국항공운항학회지 (Journal of the Korean Society for Aviation and Aeronautics)

  • 제30권4호
  • /
  • Pages.184-190
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  • 2022
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  • 1225-9705(pISSN)
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  • 2466-1791(eISSN)
한국항공운항학회 (The Korean Society for Aviation and Aeronautics)
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RATO(Rocket-Assisted Take Off) 시스템 적용을 위한 하이브리드 로켓 비단공형 연료 그레인 기초 연소특성 연구

A Study on Combustion Characteristics of Non-Circular Grain in Hybrid Rocket for RATO (Rocket-Assisted Take Off) System

  • 김수진 (한국항공대학교 항공우주 및 기계공학부) ;
  • 고수한 (한국항공대학교 항공우주 및 기계공학과) ;
  • 김설희 (한국항공대학교 항공우주 및 기계공학과) ;
  • 김경모 (한국항공대학교 항공우주 및 기계공학부) ;
  • 이성근 (한국항공대학교 항공우주 및 기계공학부) ;
  • 한예찬 (한국항공대학교 항공우주 및 기계공학부) ;
  • 문희장 (한국항공대학교 항공우주 및 기계공학부)
  • 투고 : 2022.11.28
  • 심사 : 2022.12.26
  • 발행 : 2022.12.31
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초록

In an attempt to apply hybrid rocket to the RATO (Rocket-Assisted Take Off) system, combustion characteristics of the non-circular grain were figured out in this study. Having larger combustion area, it was reconfirmed that the non-circular grain has advantages over regression rate, characteristic velocity and chamber pressure in which all gave higher values. Experiments were performed to understand the effect of the non-circular grain geometry over time where local regression rates depending on grain location were analyzed. It was found that the regression rate of five distinct locations were different. Partial conclusion driven was that these differences are due to the heat transfer caused by dissimilar distances from the flame layer. Besides, as combustion duration increased, the fuel port became circular, and the regression rate converged to a single value over the whole grain.

키워드

과제정보

본 논문은 정부(과학기술정보통신부)의 재원으로 한국연구재단-미래국방혁신기술개발사업(NRF-2020M3F6A1110342)의 지원을 받아 수행된 연구로 지원에 감사드립니다.

참고문헌

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