한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제24권3호
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  • Pages.47-58
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  • 2020
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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자발가압 아산화질소를 이용한 하이브리드 로켓의 추력제어 내탄도 해석 및 실험적 검증

Internal Ballistics Analysis and Experimental Validation of Thrust Modulation for Hybrid Rocket Using Self-Pressurizing Nitrous Oxide

  • Han, Seongjoo (Center for Reliability Engineering in Mechanical and Aerospace Industry, Korea Aerospace University) ;
  • Moon, Heejang (School of Mechanical and Aerospace Engineering, Korea Aerospace University)
  • 투고 : 2020.03.01
  • 심사 : 2020.04.25
  • 발행 : 2020.06.30
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초록

본 연구에서는 Whitmore와 Chandler의 모델을 기반으로 아산화질소를 사용하는 blow-down 방식의 하이브리드 로켓의 유량제어를 통한 추력제어 및 내탄도 해석에 대한 연구를 수행하였다. 유량제어가 포함된 아산화질소의 탱크 내 거동에 대한 예측을 수행하였으며, 해석결과와 실험결과의 일치도가 상당히 높음을 확인하였다. 또한, 추력제어 내탄도 해석의 검증을 위하여 500 N급 하이브리드 로켓을 이용한 지상연소시험을 수행하였으며, 연소실 압력 및 추력 모두 실험결과와 해석결과가 상당히 일치함을 확인하여 추력제어 성능을 예측할 수 있는 모델링 기법을 제시하였다.

In this study, a thrust modulation through oxidizer mass flow rate control and internal ballistic analysis based on Whitmore and Chandlers' models was conducted on a blow-down hybrid rocket using nitrous oxide. The tank pressure prediction considering mass flow rate control of the self-pressuring oxidizer was conducted, and the results showed good agreements with experimental results. In order to verify the internal ballistic analysis, a ground combustion test using a 500 N class hybrid rocket was conducted, and it was confirmed that the experimental results and the analytical results were quite consistent in the chamber pressure and thrust, thereby, a modeling technique capable of predicting the thrust modulation performance is proposed.

키워드

과제정보

본 논문은 국방과학연구소의 지원(UE161021GD)과 미래창조과학부의 지원(NRF-2017M1A3A3A02016561) 그리고 서울대학교 차세대 우주추진 연구센터와 연계된 미래창조과학부의 재원으로 한국연구재단의 지원을 받아 수행한 선도연구센터지원사업(NRF-2013R1A5A1073861)을 받아 수행된 연구로써 지원에 감사드립니다.

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