Japan Aerospace Exploration Agency Department of Space Transportation Engineering, Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Department of Space Transportation Engineering, Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Department of Space Transportation Engineering, Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Center for Planning and Information Systems, Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Aerodynamics Research Group, Institute of Space Technology and Aeronautics
Ryoyu Systems Co. Ltd. Engineering Solution Division
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構研究開発報告
雑誌名(英)
JAXA Research and Development Report
巻
JAXA-RR-07-035
発行年
2008-02-29
抄録（英）
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.
流体・壁面後退量連成解析によるノズル壁後退量評価
63804000.pdf
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