TY - GEN
T1 - A study on high performance hybrid rocket engine with multi-section swirl injection method for space propulsion system
AU - Aso, Shigeru
AU - Tani, Yasuhiro
AU - Saiga, Tani 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. Also the present authors would like to express their thankfulness to Mr. Kazuya Komori, Tomohiro Yamasaki, and Hiroshi Tada for their excellent support to the present study.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - A new method with multi-section swirl injection method is proposed in order to improve fuel regression rate of hybrid rocket engine. The new method is to introduce swirling flow through injector ports, which are placed at several cross-sections along the fuel grain. In the present study, combustion tests for several grain types have been conducted to clarify influences of difference in the number and direction of swirl on the regression rate. Visualization of combustion chamber of hybrid rocket engines has been conducted and swirling turbulent flow has been observed. Also, throttling of hybrid rocket engine has been conducted successfully. To realize Multi-Section Swirl Injection Method for real flight, two-module type flight engine with swirl injection has been proposed and applied to flight experiment. Hybrid rocket engine with multi-section swirl injection method has been successfully tested under 2G acceleration environment.
AB - A new method with multi-section swirl injection method is proposed in order to improve fuel regression rate of hybrid rocket engine. The new method is to introduce swirling flow through injector ports, which are placed at several cross-sections along the fuel grain. In the present study, combustion tests for several grain types have been conducted to clarify influences of difference in the number and direction of swirl on the regression rate. Visualization of combustion chamber of hybrid rocket engines has been conducted and swirling turbulent flow has been observed. Also, throttling of hybrid rocket engine has been conducted successfully. To realize Multi-Section Swirl Injection Method for real flight, two-module type flight engine with swirl injection has been proposed and applied to flight experiment. Hybrid rocket engine with multi-section swirl injection method has been successfully tested under 2G acceleration environment.
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U2 - 10.2514/6.2018-1415
DO - 10.2514/6.2018-1415
M3 - Conference contribution
AN - SCOPUS:85044576351
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -