510 衝突噴流式ハイブリッドロケットの点火特性および燃焼安定性(北海道における宇宙活動II)(オーガナイズドセッション(d)北海道における宇宙活動)

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. Previous researches with cylindrical PMMA blocks as fuel and gas oxygen as oxidizer revealed that the regression rates of forward ends increase due to the effect of impinging jet. In the present research, LOX was employed as oxidizer and ignition and combustion characteristics are investigated. Additionally, we test a new technique, which reconstruct a fuel consumption rate from the chamber pressure history of test firing is proposed. As the result, good ignition characteristics and steady combustion with liquid oxygen were confirmed. And reconstructed fuel weight histories agreed well with experimental results.
社団法人日本機械学会の論文
2000-09-25