Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Effects of Solid Propellant Cases on the Thermal Response of Nozzle Liner

노즐 내열재 열반응에 미치는 고체 추진제 연소가스의 영향

  • 황기영 (국방과학연구소 추진기관부) ;
  • 임유진 (국방과학연구소 추진기관부) ;
  • 함희철 (국방과학연구소 추진기관부) ;
  • 강윤구 (국방과학연구소 추진기관부) ;
  • 배주찬 (국방과학연구소 추진기관부)
  • Published : 2007.04.30
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Abstract

The thermal response characteristics of nozzle liner for a solid rocket motor applying highly aluminized PCP or HTPB propellant with slotted tube grain have been investigated. The SEM photographs of aluminum oxide particles taken from nozzle liner show that the PCP propellant with the finer and less contents of oxidizer can offer greater possibility for increasing aluminum agglomeration than the HTPB propellant. The PCP propellant shows locally greater mechanical erosion at 4 circumferential areas of the nozzle entrance in line with grain slot due to the impingement of large particles, but the HTPB propellant shows greater thermochemical ablation at the nozzle blast tube, the throat insert and the exit cone because of relatively much more mole fraction of $H_2O\;and\;CO_2$ in combustion gases.

슬랏이 있는 튜브형 그레인 형상의 알루미늄 함유 PCP계 또는 HTPB계 추진제를 충전한 고체 추진기관에 대해 노즐 내열재의 열반응 특성을 분석하였다. 노즐 내열재에서 채취한 산화알루미늄 입자의 SEM 사진을 통해 상대적으로 크기가 작고 저 함량의 산화제를 포함한 PCP계 추진제는 HTPB계 추진제보다 알루미늄 분말들이 응집될 가능성이 크다는 것을 확인할 수 있었다. PCP계 추진제를 적용한 경우에는 그레인 슬랏과 일치하는 노즐 축소부 내열재의 원주방향 4개 영역에서 큰 입자의 산화알루미늄 충돌로 인해 국부적으로 삭마가 많았지만 HTPB계 추진제는 연소가스내 $H_2O$ 및 $CO_2$의 몰분율이 상대적으로 많음으로 인해 노즐 토출관, 목삽입재 및 확대부 내열재에서 화학반응으로 인한 삭마가 많았다.

Keywords

References

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