720 衝突噴流式ハイブリッドロケットのフライトモデル設計のための地上燃焼試験(OS7-6 航空宇宙推進(流体,燃焼))(OS7 北海道における航空宇宙工学研究の進展と未来)

概要

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The authors have proposed a new fuel configuration to overcome defects of conventional hybrid rockets such as low thrust level and low combustion efficiency. This new fuel configuration allows mixing and combustion to occur around jet-impinging points on forward ends of solid fuels. In the previous researches with cylindrical PMMA blocks as fuel, LOx was employed as oxidizer and ignition and combustion characteristics are investigated. As the result, good ignition characteristics and steady combustion with LOx were confirmed. In the present research, the engineering model of jet-impinging hybrid rocket is designed on the basis of the results of the previous researches and conduct the static test firings with it. Based on the results of the tests, the parameters which are requisite for designing the flight model engine of jet-impinging hybrid rocket are determined.
社団法人日本機械学会の論文
2001-09-25