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

The Korean Society for Aviation and Aeronautics (한국항공운항학회)
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Effect of Combustors and Propellant Parameters on the L* Instability of Solid Rocket Motors

연소실 및 추진제 변화에 따른 고체로켓 모터의 L* 불안정에 관한 연구

  • 이동희 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 류승현 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 주성민 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 김준성 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
  • 문희장 (한국항공대학교 항공우주 및 기계공학부) ;
  • 성홍계 (한국항공대학교 항공우주 및 기계공학부) ;
  • 양준서 (국방과학연구소)
  • Received : 2015.11.02
  • Accepted : 2015.12.10
  • Published : 2015.12.31
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Abstract

In this paper, a theoretical study of low frequency non acoustic instability, the $L^*$ instability, of a solid rocket motor is investigated. The $L^*$ stability criterion is determined by analysing the $L^*$ stability curves of two very distinct propellants for five different geometrical combustors. The $L^*$ instability of two extreme fuels showed totally different behavior in terms of operating pressure of the combustor. A parametric study on the stability for different chamber volume and different throat area keeping constant $L^*$ is conducted and analyzed. It was found that one of the main parameters, the non-dimensional critical characteristic time, requires an enough margin from the critical $L^*$ stability curve.

Keywords

References

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