Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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An Analysis and Reduction Design of Combustion Instability Generated in Hybrid Rocket Motor

하이브리드 로켓 모터의 연소불안정 분석 및 저감 설계

  • Lee, Jungpyo (Aerospace Engineering, Universidade de Brasilia) ;
  • Rhee, Sunjae (R&D Planning & Coordination Division, Korea Aerospace Research Institute) ;
  • Kim, Jinkon (School of Aerospace & Mechanical Engineering, Korea Aerospace University) ;
  • Moon, Heejang (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
  • Received : 2013.12.11
  • Accepted : 2014.07.11
  • Published : 2014.08.01
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Abstract

In this paper, the mechanism of the combustion instability which may occur in a hybrid rocket motor with a diaphragm was studied. And the new design for a hybrid motor grain was suggested. It could increase a regression rate of solid fuel, and reduce a large pressure oscillation in a hybrid rocket motor with a diaphragm. It was confirmed that the main mechanism of a large pressure oscillation was hole-tone, and it was caused by a collision between a diaphragm and a vortex which was generated in a pre-chamber. And 'Stepped Grain' design which had the mechanism for high regression rate in a motor with a diaphragm and could reduce a combustion instability was suggested.

본 연구에서는 다이아프램(diaphragm)을 설치한 하이브리드 로켓에서 발생하는 연소불안정의 발생 메커니즘을 알아보고, 고체연료의 연소율은 증가하면서 연소불안정은 줄일 수 있는 그레인 설계를 제안하였다. 고체연료의 연소율을 증진시키기 위해 다이아프램을 설치한 하이브리드 로켓 모터에서 관찰되는 큰 연소불안정의 가진 요인은 전방 연소실에서 생성된 와류가 후방의 다이아프램에 부딪치면서 나타나는 Hole-tone으로 판단된다. 또한 다이아프램의 고연소율 발생 메카니즘을 적용하면서 연소불안정은 줄일 수 있는 'Stepped Grain'을 제안하였다.

Keywords

References

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