TY - GEN
T1 - Flight Demonstration of Detonation Engine System Using Sounding Rocket S-520-31
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
AU - Goto, Keisuke
AU - Matsuoka, Ken
AU - Matsuyama, Koichi
AU - Kawasaki, Akira
AU - Watanabe, Hiroaki
AU - Itouyama, Noboru
AU - Ishihara, Kazuki
AU - Buyakofu, Valentin
AU - Noda, Tomoyuki
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
AU - Nakata, Daisuke
AU - Uchiumi, Masaharu
AU - Habu, Hiroto
AU - Takeuchi, Shinsuke
AU - Arakawa, Satoshi
AU - Masuda, Junichi
AU - Maehara, Kenji
AU - Nakao, Tatsuro
AU - Yamada, Kazuhiko
N1 - Funding Information:
This research was partially supported by Research-and-Development Grant Program (Engineering) in Institute of Space and Astronautical Science (ISAS) at Japan Aerospace Exploration Agency (JAXA) and Japan Society for the Promotion of Science (JSPS) KAKENHI (grant numbers 19H05464). The detonation engine system was designed and fabricated with the participation of NETS Inc., Yamamoto Machinery Design Co., Kawasho Design Co., Meiji Electric Industries Co., Ltd. The authors thank Dr. Kazuyuki Higashino, Prof. Takuma Endo, and Prof. Kazuhiro Ishii for fruitful discussion. The authors also thank other present or former laboratory members for their contribution to this project: Yuichi Kato, Junpei Nishimura, Takato Ukai, Koyo Kikuchi, Haruna Taki, Yuki Hayamizu, Junichi Higashi, Taihei Yamada, Tomoya Inakawa, Akiya Kubota, Toshiki Daicho, Koutaro Hotta, Masato Yamaguchi, Shun Watanabe, Motomu Asahara, Masaya Tanaka, Ryuya Yokoo, Juhoe Kim, Yuki Akimoto, Tomoyuki Sato, Satoru Sawada, Shiro Ito, Kose Ota, Kentaro Yoneyama, Yuse Kikuchi, Tomoaki Kimura, Kotaro Nakata, Karin Hattori, and Shinnichi Sugiura at Nagoya University and Tomoyuki Takano, Koki Arimatsu, Kasumi Hayashi, Keisuke Ikeda, Satoshi Inazumi, Kenta Mori, Genta Sugahara, Masaya Sumiyoshi, Hiromitsu Yagihashi, and Kazuki Yasuda at Muroran Institute of Technology.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - To create a new flyable propulsion system, Detonation Engine System (DES) has developed which can be stowed in the sounding rocket S-520-31. This paper focused on the first flight demonstration of RDE in space environment, which is integrated into DES, using S-520-31. The flight result was compared with the ground test data to validate its performance. In the flight experiment, the stable combustion of the RDE with aerospike nozzle was observed by onboard digital and analog cameras. With time-averaged mass flow of 182 ± 11 g/s and equivalence ratio of 1.2 ± 0.2, the RDE generated the time-averaged-thrust of 518 N, and the specific impulse achieved 290 ± 18 s, which is almost identical to the ideal value of constant pressure combustion. Due to the RDE combustion, the angular velocity increased by 5.7 deg/s for total, and the time-averaged torque during 6 s of operation was 0.26 N∙m. The high frequency sampling data identified the detonation frequency during record time as 20 kHz in the flight, which was confirmed in the DES ground test through the high frequency sampling data analysis and high-speed video imaging.
AB - To create a new flyable propulsion system, Detonation Engine System (DES) has developed which can be stowed in the sounding rocket S-520-31. This paper focused on the first flight demonstration of RDE in space environment, which is integrated into DES, using S-520-31. The flight result was compared with the ground test data to validate its performance. In the flight experiment, the stable combustion of the RDE with aerospike nozzle was observed by onboard digital and analog cameras. With time-averaged mass flow of 182 ± 11 g/s and equivalence ratio of 1.2 ± 0.2, the RDE generated the time-averaged-thrust of 518 N, and the specific impulse achieved 290 ± 18 s, which is almost identical to the ideal value of constant pressure combustion. Due to the RDE combustion, the angular velocity increased by 5.7 deg/s for total, and the time-averaged torque during 6 s of operation was 0.26 N∙m. The high frequency sampling data identified the detonation frequency during record time as 20 kHz in the flight, which was confirmed in the DES ground test through the high frequency sampling data analysis and high-speed video imaging.
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UR - http://www.scopus.com/inward/citedby.url?scp=85122587921&partnerID=8YFLogxK
U2 - 10.2514/6.2022-0232
DO - 10.2514/6.2022-0232
M3 - Conference contribution
AN - SCOPUS:85122587921
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
Y2 - 3 January 2022 through 7 January 2022
ER -