730 日本初小型ハイブリッドロケットの打ち上げ : 開発と実験結果・今後の課題(OS7-4 基調講演)(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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Burning tests of a swirling-oxidizer-type hybrid rocket engine with the PMMA/O_2 propellant, which were conducted at large O_2 mass fluxes and high chamber pressures, showed that rapid ignition and stable combustion occurred and overall fuel regression rate with swirl increased up to 2.7 times of that without swirl. A full-scale engine achieved a maximum thrust of 692 [N] and specific impulse of 263 [s]. Using this engine, a small hybrid rocket that was 1.8 [m] in length and 15.4 [kg] in mass was designed and fabricated. It was launched from Taiki-cho, Hokkaido, Japan, and reached an altitude of about 600 [m]. The successful launch demonstrated the advantages of this hybrid rocket engine with a swirling oxidizer flow and a maturity level of the propulsion.
社団法人日本機械学会の論文
2001-09-25