@article{1a9940a2d8ad44c8b5cc262cb9ee0ee0,
title = "Development of an S-Shaped Pulse Detonation Engine for a Sounding Rocket",
abstract = "This paper presents the results of an S-shaped pulse detonation engine (PDE) ground firing test in the form of a detonation engine system. The world{\textquoteright}s first technology demonstration of PDE in space using a sounding rocket is planned, and the aim is to control the rocket spin rate in the axial direction using pulsed detonation. The PDE operation at full sequence was successful. The despin rate change of the rocket between continuous oxygen supply and successful PDE operation is expected to be 0.95 deg ∕s per run. This change in despin rate can be measured by an onboard gyro sensor, making the system flyable. The test results were compared with data from thrust measurement tests conducted in a laboratory, the results of which confirmed the thrust generation under an ambient pressure of 0.5 0.1 kPa. The average thrust values in the thrust measurement experiments showed good agreement of 101 3% with a quasi-steady-state model introduced to predict the PDE thrust. These results demonstrate the feasibility of the newly developed PDE and its system as the world{\textquoteright}s first technology demonstration of detonation propulsion in space.",
author = "Valentin Buyakofu and Ken Matsuoka and Koichi Matsuyama and Akira Kawasaki and Hiroaki Watanabe and Noboru Itouyama and Keisuke Goto and Kazuki Ishihara and Tomoyuki Noda and Jiro Kasahara and Akiko Matsuo and Ikkoh Funaki and Daisuke Nakata and Masaharu Uchiumi and Hiroto Habu and Shinsuke Takeuchi and Satoshi Arakawa and Junichi Masuda and Kenji Maehara",
note = "Funding Information: This research was partially supported by Research and Development Grant Program (Engineering) of the Institute of Space and Astronautical Science of the Japan Aerospace Exploration Agency and the Japan Society for the Promotion of Science KAKENHI (grant number 19H05464). The detonation engine system was designed and manufactured with the participation of Shuichi Nakamura, Shinji Toyonaga, Osamu Harada, Hidefumi Kawano, Fumitaka Yamamoto, Syouji Kawamoto, and Kazuyuki Higashino at Nakamura Engineering & Trading Service, Inc., and Naoya Mita, Hiromi Jindo, Ichiro Doyama, and Tatsuya Kato at Meiji Electric Industries, Co., Ltd. The authors also thank other laboratory members for their contributions to this study: Ryuya Yokoo, Shiro Ito, Kosei Ota, and Kotaro Nakata at Nagoya University, and Tomoyuki Takano, Koki Arimatsu, Masaya Sumiyoshi, Kasumi Hayashi, Keisuke Ikeda, and Genta Sugahara at the Muroran Institute of Technology. Publisher Copyright: {\textcopyright} AIAA International. All rights reserved.",
year = "2022",
doi = "10.2514/1.A35200",
language = "English",
volume = "59",
pages = "850--860",
journal = "Journal of Spacecraft and Rockets",
issn = "0022-4650",
publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",
number = "3",
}