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title流体・壁面後退量連成解析によるノズル壁後退量評価
Other TitleEstimation of recession amount of nozzle wall using coupled fluid/thermochemical approach
Author(jpn)大門 優; 嶋田 徹; 坪井 伸幸; 高木 亮治; 藤田 和央; 竹川 国之
Author(eng)Daimon, Yu; Shimada, Toru; Tsuboi, Nobuyuki; Takaki, Ryoji; Fujita, Kazuhisa; Takekawa, Kuniyuki
Author Affiliation(jpn)宇宙航空研究開発機構 宇宙科学研究本部 宇宙輸送工学研究系; 宇宙航空研究開発機構 宇宙科学研究本部 宇宙輸送工学研究系; 宇宙航空研究開発機構 宇宙科学研究本部 宇宙輸送工学研究系; 宇宙航空研究開発機構 宇宙科学研究本部 宇宙科学情報解析センター; 宇宙航空研究開発機構 総合技術研究本部 空気力学研究グループ; 菱友システムズ エンジニアリングソリューション事業部
Author Affiliation(eng)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
Issue Date2008-02-29
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication date2008-02-29
Languagejpn
AbstractEvaluation 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.
DescriptionJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
Keywordsnozzle design; nozzle flow; nozzle geometry; rocket nozzle; throat; carbon fiber reinforced plastic; ablative material; ablation; nozzle wall; recession; solid rocket propellant; propellant combustion; computerized simulation; ノズル設計; ノズル流; ノズル形状; ロケットノズル; スロート; 炭素繊維強化樹脂; アブレーション材料; アブレーション; ノズル壁; 後退; 固体ロケット推進薬; 推進薬燃焼; 計算機シミュレーション
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1113
SHI-NOAA0063804000
Report NoJAXA-RR-07-035
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/26795


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