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 - Buyakofu, Valentin
AU - Matsuoka, Ken
AU - Matsuyama, Koichi
AU - Goto, Keisuke
AU - Kawasaki, Akira
AU - Watanabe, Hiroaki
AU - Itouyama, Noboru
AU - Ishihara, Kazuki
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 the Research-and-Development Grant Program (Engineering) in Institute of Space and Astronautical Science (ISAS) at the 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 manufactured with the participation of NETS Inc., Yamamoto Machinery Design Co., Kawamasa 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, Kosei 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 - A research team of Nagoya University, Keio University, Muroran Institute of Technology, and Institute of Space and Astronautical Science (ISAS) at Japan Aerospace Exploration Agency (JAXA) successfully conducted a space demonstration of the detonation engine system (DES) using the S-520-31 sounding rocket of JAXA/ISAS. This paper presents the results of an S-shaped pulse detonation engine (PDE) flight test. The aim of the flight is to confirm that the PDE and its system operate in space, to confirm the reproducibility of the PDE cycle, and to despin the sounding around its axis. The PDE and its system successfully operated for 14 cycles in space. The experimental plateau pressure was 80 ± 3 % of the calculated plateau pressure, suggesting that detonation occurred in 14 cycles. Pressure profile of the 14 cycles was highly reproduced as well. The average angular acceleration change of PDE operation, mixture supply, and oxygen supply were determined using gaussian distribution. The results suggested that the PDE despinned the sounding rocket by the thrust from detonation combustion, which was in good agreement with a quasi-steady-state model with an accuracy of 101 ± 15%.
AB - A research team of Nagoya University, Keio University, Muroran Institute of Technology, and Institute of Space and Astronautical Science (ISAS) at Japan Aerospace Exploration Agency (JAXA) successfully conducted a space demonstration of the detonation engine system (DES) using the S-520-31 sounding rocket of JAXA/ISAS. This paper presents the results of an S-shaped pulse detonation engine (PDE) flight test. The aim of the flight is to confirm that the PDE and its system operate in space, to confirm the reproducibility of the PDE cycle, and to despin the sounding around its axis. The PDE and its system successfully operated for 14 cycles in space. The experimental plateau pressure was 80 ± 3 % of the calculated plateau pressure, suggesting that detonation occurred in 14 cycles. Pressure profile of the 14 cycles was highly reproduced as well. The average angular acceleration change of PDE operation, mixture supply, and oxygen supply were determined using gaussian distribution. The results suggested that the PDE despinned the sounding rocket by the thrust from detonation combustion, which was in good agreement with a quasi-steady-state model with an accuracy of 101 ± 15%.
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U2 - 10.2514/6.2022-0233
DO - 10.2514/6.2022-0233
M3 - Conference contribution
AN - SCOPUS:85122678833
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
SP - 1
EP - 14
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
Y2 - 3 January 2022 through 7 January 2022
ER -