流体・壁面後退量連成解析によるノズル壁後退量評価

概要

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Evaluation of ablation of nozzle wall in solid rocket motor is studied numerically on three solid rocket motors. A coupled analysis of fluid dynamics and surface recession simulates a total ablation amount. The analysis consists of the two-dimensional axisymmetric fluid analysis and the estimation of ablation amount using a correlation equation of surface recession rate. The simulation results of total surface recession amount agree qualitatively with experimental results in Nozzle-A case. The numerical simulations estimate the erosion rate on the safe-side. The effect of shield for reactant gas from nozzle surface reaction is estimated by a simple model. This model works very well for the agreement to experimental results. However, the parameter of the model has to be decided from experimental data. This model is not sufficient for prediction of unknown rocket motor. The coupled analysis was performed on Nozzle-B and C cases in order to understand flow field and erosion mechanism.
宇宙航空研究開発機構の論文