Investigation of regression characteristics under relatively high-pressure in Axial-injection End-Burning Hybrid Rockets

Yuji Saito, Masaya Kimino, Tsuji Ayumu, Yushi Okutani, Kazunobu Omura, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata

研究成果: Conference contribution

抄録

This study is an investigation of Axial-Inection End-Burning Hybrid Rockets aimed at revealing fuel regression characteristics under relatively high pressure conditions. Firing tests were conducted using gaseous oxygen as oxidizer at chamber pressures and oxidizer port velocities ranging from 0.22 MPa to 1.05 MPa and 31 m/s to 103 m/s, respectively. The results of fifteen static firing tests show that fuel regression rate increases as the chamber pressure increases, and regression rates ranged from approximately 1.1 mm/s at 0.25 MPa to 5.4 mm/s at 0.71 MPa. Furthermore, it is observed that the fuel regression rate is not influenced by oxidizer port velocity. The athours encountered a problem refered to as backfiring in this paper, and developed a calculation model to investigate this problemanalytically. The calculation model explains why the back-firing problem tends to occur in relatively high-pressure conditions, and leads to the conclusion that increasing nozzle throat diameter is an effective means of preventing back-firing from occuring.

本文言語English
ホスト出版物のタイトル53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624105111
DOI
出版ステータスPublished - 2017
外部発表はい
イベント53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 - Atlanta, Georgia
継続期間: 2017 7 102017 7 12

出版物シリーズ

名前53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017

Conference

Conference53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017
国/地域Georgia
CityAtlanta
Period17/7/1017/7/12

ASJC Scopus subject areas

  • 工学(全般)

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