Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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A Study on the Combustion Instability of the Hybrid Rocket Motor with a Diaphragm

다이아프램이 설치된 하이브리드 로켓 모터의 연소불안정 연구

  • Lee, Jungpyo (Technical Support, Flowmaster Korea) ;
  • Kim, Youngnam (Flow and Noise) ;
  • Kim, Jinkon (School of Aerospace & Mechanical Engineering, Korea Aerospace University) ;
  • Moon, Heejang (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
  • Received : 2013.08.27
  • Accepted : 2013.11.15
  • Published : 2013.12.01
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Abstract

In this paper, the main cause on excitation of the combustion instability which may occur in the hybrid rocket motor with a diaphragm was studied. Hybrid rocket motor propulsion tests considering various experimental conditions such as with a diaphragm or not, a diameter of diaphragm, oxidizer mass flow rate, fuel length, etc were performed, and the combustion visualization for the inside of a hybrid rocket motor with a diaphragm was performed. With these experimental results, it was confirmed that the main cause of a large excitation was the hole-tone, and it was shown that the hole-tone model can be predicted experimental primary pressure oscillation frequency quite well.

본 연구에서는 다이아프램이 설치된 하이브리드 로켓 모터에서 발생하는 큰 압력진동의 가진 요인을 분석하였다. 다이아프램 유 무와 다이아프램 직경, 산화제 유량, 연료 길이 등의 다양한 실험조건을 고려하여 하이브리드 로켓 모터 추진시험을 수행하였고, 하이브리드 로켓 모터 가시화 장치를 이용하여 다이아프램이 삽입된 연소기의 내부 연소장을 가시화 하였다. 이러한 실험을 통해 주요 연소실 압력 가진 요인은 hole-tone인 것으로 판단되고, hole-tone 모델로 예측한 주파수와 추진 시험을 통해 획득한 주요 압력진동 주파수가 잘 일치함을 확인하였다.

Keywords

References

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  1. An Analysis and Reduction Design of Combustion Instability Generated in Hybrid Rocket Motor vol.18, pp.4, 2014, https://doi.org/10.6108/KSPE.2014.18.4.018