항공우주시스템공학회지 (Journal of Aerospace System Engineering)

  • 제15권6호
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  • Pages.10-18
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  • 2021
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  • 1976-6300(pISSN)
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  • 2508-7150(eISSN)
항공우주시스템공학회 (The Society for Aerospace System Engineering)
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Numerical Study of Ablation Phenomena of Flame Deflector

  • Lee, Wonseok (Missile Research Institute, Agency for Defense Development) ;
  • Yang, Yeongrok (Missile Research Institute, Agency for Defense Development) ;
  • Shin, Sangmok (Missile Research Institute, Agency for Defense Development) ;
  • Shin, Jaecheol (Missile Research Institute, Agency for Defense Development)
  • 투고 : 2021.07.09
  • 심사 : 2021.09.15
  • 발행 : 2021.12.31
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초록

A flame deflector prevents a launch system from thermal damage by deflecting the exhaust flame of the launch vehicle. During the deflection of the flame, the flame deflector is subjected to a high-temperature and high-pressure flow, which results in thermal ablation damage at the surface. Predicting this ablation damage is an essential requirement to ensure a reliable design. This paper introduces a numerical method for predicting the ablation damage phenomena based on a one-way fluid-structure interaction (FSI) analysis. In the proposed procedure, the temperature and convective heat transfer coefficient of the exhaust flame are calculated using a fluid dynamics analysis, and then the ablation is calculated using a finite element analysis (FEA) based on the user-subroutine UMESHMOTION and Arbitrary Lagrangian-Eulerian (ALE) adaptive mesh technique in ABAQUS. The result of such an analysis was verified by comparison to the ablation test result for a flame deflector.

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참고문헌

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