복사 효과를 고려한 고체추진 로켓의 점화 현상 해석

Abstract

A numerical simulation is performed to analyze the ignition transient in a solid rocket motor by employing time-dependent compressible SIMPLER algorithm for gas phase governing equations and FVM for radiative transfer equation. Two dimensional conduction equation for propellant grain is also coupled. The standard k-ε model with wall function is used for turbulence. A reasonably good agreement with the experiment is obtained in predicting a variation of head end pressure. Based on this comparison, a detailed development of unsteady flow and temperature fields obtained is helpful for understanding the physical phenomena involved. Especially, the radiation is found to play a significant role in igniting the solid propellant by promoting the heat feedback to propellant surface.