Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Numerical Study on the Unsteady Solid Rocket Propellant Combustion with Erosive Burning

침식효과를 고려한 고체 로켓 추진제의 비정상 연소에 관한 수치해석

  • Published : 2009.08.01
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Abstract

A numerical modelling was performed to predict unsteady combustion processes for the AP/HTPB/Al propellant in a solid rocket motor. Its results were compared with the experimental data. Temporal pressure development was found to match quite well with measured data. A change in propellant surface was traced using the moving grid. The propellant thickness change was also observed to confirm the erosive burning effect.

AP/HTPB/Al 연료를 사용하는 고체 로켓 모터에 대한 수치해석을 수행하였다. 그 결과는 실험 데이터와 비교하였다. 수치적으로 해석한 시간에 따른 연소실 압력 변화는 측정값과 잘 일치함을 확인할 수 있었다. 고체 추진제 표면의 변화는 이동 격자를 사용하여 추적하였다. 침식 현상을 확인하기 위해서 시간에 따른 추진제 두께의 변화를 확인하였다.

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References

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