TY - GEN
T1 - Throttling capability and LOX vaporization for hybrid rocket engine with multi-section swirl injection method
AU - Aso, Shigeru
AU - Tani, Yasuhiro
AU - Yamashita, Masato
AU - Komori, Kazuya
AU - Yamasaki, Tomohiro
AU - Saiga, Shohei
AU - Arakawa, Ryohei
AU - Shimada, Toru
N1 - Funding Information:
The research is supported by the Hybrid Rocket Research Working Group (HRrWG) of Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency. The authors thank members of HRrWG for their helpful discussion.
Publisher Copyright:
Copyright © 2017 by the International Astronautical Federation (IAF). All rights reserved.
PY - 2017
Y1 - 2017
N2 - 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.
AB - 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.
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M3 - Conference contribution
AN - SCOPUS:85051484377
SN - 9781510855373
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 8624
EP - 8628
BT - 68th International Astronautical Congress, IAC 2017
PB - International Astronautical Federation, IAF
T2 - 68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017
Y2 - 25 September 2017 through 29 September 2017
ER -