Throttling capability and LOX vaporization for hybrid rocket engine with multi-section swirl injection method

Shigeru Aso, Yasuhiro Tani, Masato Yamashita, Kazuya Komori, Tomohiro Yamasaki, Shohei Saiga, Ryohei Arakawa, Toru Shimada

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

A new hybrid rocket combustion method which can improve the fuel regression rate more than that of conventional method. The new method is named as Multi-Section Swirl Injection Method, which generates swirling flows at some cross-sections in combustion chamber. Combustion experiments with carefully tuned oxygen injections to keep each O/F at optimum value has been successfully conducted. Also throttling experiments, vaporization experiments of liquid oxygen, flight experiments with multi-section swirl injection method have been successfully. The results shows proposed method of vaporization of liquid oxygen is useful and also hybrid rocket engine with Multi-Section Swirl Injection Method can operate with acceleration environment.

Original languageEnglish
Title of host publication68th International Astronautical Congress, IAC 2017
Subtitle of host publicationUnlocking Imagination, Fostering Innovation and Strengthening Security
PublisherInternational Astronautical Federation, IAF
Pages8624-8628
Number of pages5
ISBN (Print)9781510855373
Publication statusPublished - Jan 1 2017
Event68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017 - Adelaide, Australia
Duration: Sep 25 2017Sep 29 2017

Publication series

NameProceedings of the International Astronautical Congress, IAC
Volume13
ISSN (Print)0074-1795

Other

Other68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017
CountryAustralia
CityAdelaide
Period9/25/179/29/17

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Astronomy and Astrophysics
  • Space and Planetary Science

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  • Cite this

    Aso, S., Tani, Y., Yamashita, M., Komori, K., Yamasaki, T., Saiga, S., Arakawa, R., & Shimada, T. (2017). Throttling capability and LOX vaporization for hybrid rocket engine with multi-section swirl injection method. In 68th International Astronautical Congress, IAC 2017: Unlocking Imagination, Fostering Innovation and Strengthening Security (pp. 8624-8628). (Proceedings of the International Astronautical Congress, IAC; Vol. 13). International Astronautical Federation, IAF.