open access

https://doi.org/10.14943/doctoral.k14875

https://hdl.handle.net/2115/86543

CAMUI型ハイブリッドロケットの燃料後退モデルにおけるスケール則の適用性

英語

2022-03-24

Hokkaido University

xix, 107p.

Hybrid rocket engines have several advantages over liquid or solid engines but have traditionally seen limited use due to a low thrust-to-weight ratio. The Cascading Multi-Stage Impinging jet (CAMUI) hybrid rocket engine addresses this by using a series of impinging jets and fountain-like flow paths to improve mixing and increase heat transfer to the solid fuel surface. This thesis investigates the scaling of the CAMUI regression model over an extensive engine size range for the first time, comparing the model to actual firing data from over 30 hybrid rocket firing tests, ranging from 100 mm-diameter-2.5 kN-class engines to 400 mm-diameter-40 kN commercial class engines. With the development of a time-stepped regression simulator, identification and quantification of potential regression simulation uncertainties were performed. Burn time, specifically the effect of long start-up transients, was identified as the most critical. Further investigation into the impact of the transient burn time resulted in the proposed method of using burn time equivalent. This method considerably reduced the errors arising from the long start-up transients. Though done for the CAMUI engine, it was shown to be valid for other hybrid rocket engines. Lastly, with the proposed regression model corrections implemented, the simulator was used to design the successfully fired 40 kN-class engine. The developed model showed good scalability when evaluating the overall regression simulation model in the order of magnitude scaling range of 100 mm-diameter-2.5 kN-class engines to 400 mm-diameter-40 kN. This validates the scalability of the CAMUI concepts as well as its regression modeling to large-scale engines, opening the door for commercial implementation of CAMUI for suborbital and orbital-class rockets.

2022-03-24

甲第14875号

博士(工学)

(主査) 教授 永田 晴紀, 教授 藤田 修, 教授 大島 伸行

工学院（機械宇宙工学専攻）

博士論文

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