A study on performance improvement of paraffin fueled hybrid rocket engines with multi-section swirl injection method

K. Araki, Y. Hirata, S. Ohyama, K. Ohe, Shigeru Aso, Yasuhiro Tani, T. Shimada

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

2 被引用数 (Scopus)

抄録

Recently, hybrid rockets have attracted a lot of interests, because it has main some advantages of low cost, safety, and thrust throttling. On the other hand, launching practical satellites, hybrid rocket has technical problems to overcome, such as low fuel regression rate and low combustion effic iency. In order to improve fuel regression rate and combustion efficiency, a new method with multi-section swirl injection was proposed. In the previous study, it was proved that this method was very effective in increasing fuel regression rate, combustion efficiency, and thrust of hybrid rocket engines. Especially, the fuel regression rate for paraffin fuels with multi-section swirl injection method reaches to about 3 to 10 times higher than that of the no-swirl conventional method. Additionally, deep grooves like erosion are observed on the surface around injector ports of fuel grains after combustion tests. In this paper, combustion tests for several grain types were conducted to clarify influences of difference in the number and diameter of injector ports on the regression rate.

本文言語英語
ホスト出版物のタイトル49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
出版ステータス出版済み - 2013
イベント49th AIAA/ASME/SAE/ASEE Joint PropulsionConference - San Jose, CA, 米国
継続期間: 7 14 20137 17 2013

その他

その他49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
国/地域米国
CitySan Jose, CA
Period7/14/137/17/13

All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 制御およびシステム工学
  • 電子工学および電気工学

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