Nagoya University, Press Release2021.8.19

World First! Successful Space Flight
Demonstration of Detonation Enginesfor Deep Space Exploration
A research group at the Institute of Materials and Systems for Sustainability, Nagoya
University and the Graduate School of Engineering, Nagoya University, in collaboration withKeio University, Institute of Space and Astronautical Science (ISAS) of the Japan Aerospace
Exploration Agency (JAXA), and the Muroran Institute of Technology, has successfully
demonstrated a detonation engine in space flight. This is the world's first successful
demonstration of a detonation engine in space flight.
The detonation engine system developed in this study was loaded onto the mission sectionof the sounding rocket S‐520‐31 and launched from the JAXA Uchinoura Space Center at 5:30
a.m. on July 27, 2021. After the separation of the first stage rocket, the rotating detonationengine and pulse detonation engine were successfully operated in space, and photo images,
pressure, temperature, vibration, position, and attitude data were acquired by telemetry andRATS (Reentry and Recovery Module with Deployable Aeroshell Technology for Sounding
Rocket Experiment). The fuel is methane and the oxidizer is oxygen.
The detonation engine generates detonation and compression waves at extremely highfrequencies (1–100 kHz) to drastically increase reaction speed, leading to radical reduction ofrocket engine weights and high performance by easy generation of thrust. The success of thisspace flight demonstration will bring the detonation engine much closer to practical use as akick motor for deep space exploration, and as a first and second stage engine for rockets.
The results of this research will be published in academic journals after detailed analysis of
the flight data. The development of the detonation engine system was carried out incooperation with Nets Co., Ltd., and Meiji Electric Industries Co., Ltd.
This research was supported by the Strategic Development Research (Engineering) of theAdvisory Committee for Space Engineering, Institute of Space and Astronautical Science, JAXA,from 2014–2021, the NEDO Feasibility Study Program on Energy and New Environmental
Technology from 2014–2016, and the JSPS Grant‐in‐Aid for Specially Promoted Research from2019–2023.
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Nagoya University, Press Release2021.8.19

Major points
1. We present the world's first successful space flight demonstration of detonation engines.
2. The rotating detonation engine (RDE) and pulse detonation engine (PDE) were successfullyoperated in space under the flight environment, and the operating data of these engines weresuccessfully acquired.
3. The results of this study show that the detonation engine is very close to practical use as anaerospace engine, such as a kick motor for deep space exploration.
Research background and content
The detonation engine generates detonation and compression waves at extremely highfrequencies (1–100 kHz) to dramatically increase reaction speed, thereby enabling radical
reduction of the weight of rocket engines and increasing their performance by enabling easy
generation of thrust. At present, research is actively underway in Japan, North America, Europe,Asia, and Australia with a view to commercialization of a high‐performance engine for space use.
This joint research group succeeded in achieving the world's first space flight demonstrationof a detonation engine. The detonation engine system developed in this study was loaded onto
the mission section of the sounding rocket S‐520‐31, and launched at 5:30 a.m. on July 27, 2021
from the JAXA Uchinoura Space Center (USC). After the separation of the first stage rocket, theRDE (6‐sec operation, 500‐N thrust) and PDE (2‐sec operation x 3 times) operated normally inspace, and images, pressure, temperature, vibration, position, and attitude data were acquiredby telemetry and recovery module RATS. The fuel is methane and the oxidizer is oxygen.

Fig. 1 The moment the world's first rotating detonation engine (RDE) began operations in space. The ellipticalluminous area (left) is the combustor of the double‐cylinder rotating detonation engine. On the right is animage of the Earth taken from space. Image data was recovered by RATS. [Credit: Nagoya University, JAXA]

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Fig. 2 Photograph of the Detonation Engine System (DES). [Credit: Nagoya University]

Fig. 3 Schematic diagram of the DES. From left to right: DES avionics (DES‐PDU, DES‐MCU, PI‐BAT‐L), methane,oxygen and nitrogen gas tanks (propellant tanks), gas supply system, PDE, RDE, DES cameras and Ku‐TV
antenna. [Credit: Nagoya University]3

Nagoya University, Press Release2021.8.19

Fig. 4 Ground‐based combustion test of the DES at the Shiraoi test site of Muroran Institute of Technology.
[Credit: Nagoya University].

Significance of the results
The success of this space flight demonstration will bring the detonation engine much closer
to practical use as a kick motor for deep space exploration, and as a first and second stage engine
for rockets.
Existing rocket engines will be replaced by detonation engines, because detonation engines
are lighter and have higher performance. In other words, the results of this research will be acatalyst for major changes in aerospace engines and systems.
Researcher Contact Information
Nagoya University
Institute of Materials and Systems for Sustainability
Jiro Kasahara, Professor
TEL: +81‐52‐789‐4404
E‐mail: kasahara@nuae.nagoya‐u.ac.jp
Nagoya University team members researching detonation engine system (DES) part
Jiro Kasahara, Professor
Koichi Matsuyama, Designated Professor
Ken Matsuoka, Associate Professor
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Akira Kawasaki, Assistant Professor
Hiroaki Watanabe, Assistant Professor
Noboru Itouyama, Designated Assistant Professor
Keisuke Goto, Designated Assistant Professor
Kazuki Ishihara, Graduate Student
Valentin Buyakofu, Graduate Student
Tomoyuki Noda, Graduate Student
Yuki Akimoto, Graduate Student
Koyo Kikuchi, Graduate Student
Related information
Article on ISAS/JAXA web site (in Japanese)
https://www.isas.jaxa.jp/topics/002693.html
Propulsion and Energy Systems Engineering Research Group, Nagoya University
http://www.prop.nuae.nagoya‐u.ac.jp/index.html
Related published journal papers of this project
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S. Sawada, K. Goto, K. Ishihara, A. Kawasaki, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki, Experimental
Study of Torque Around the Axial Direction on Rotating Detonation Engines, Journal of Propulsion andPower (accepted 2nd July, 2021)
K. Goto, Y. Kato, K. Ishihara, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki, D. Nakata, K. Higashino, and N.
Tanatsugu, Thrust Validation of Rotating Detonation Engine System by Moving Rocket Sled‐Test, Journal ofPropulsion and Power, Vol.37, No. 3, 2021, pp.419‐425.
http://arc.aiaa.org/doi/abs/10.2514/1.B38037
K. Matsuoka, M. Tanaka, T. Noda, A. Kawasaki, J. Kasahara, Experimental Investigation on a Rotating
Detonation Cycle with Burned Gas Backflow，Combustion and Flame, Vol.225, 2021, pp.13‐19.
https://doi.org/10.1016/j.combustflame.2020.10.048
R. Yokoo, K. Goto, J. Kasahara, V. Athmanathan, J. Braun, G. Paniagua, T. Meyer, A. Kawasaki, K. Matsuoka, A.
Matsuo, I. Funaki, Experimental Study of Internal Flow Structures in Cylindrical Rotating Detonation Engines,
Proceedings of the Combustion Institute, Vol.38, No. 3, 2021, pp.3759‐3768.
https://doi.org/10.1016/j.proci.2020.08.001
M. Yamaguchi, K. Matsuoka, A. Kawasaki, J. Kasahara, H. Watanabe, A. Matsuo, Investigation of combustion
modes and pressure of reflective shuttling detonation combustor, Proceedings of the Combustion Institute,Vol.38, No. 3, 2021, pp.3615‐3622.
https://doi.org/10.1016/j.proci.2020.07.064
R. Yokoo, K. Goto, J. Kim, A. Kawasaki, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki, Propulsion
Performance of Cylindrical Rotating Detonation Engine, AIAA Journal , Vol. 58, No. 12, 2020, pp.5107‐5116.
http://arc.aiaa.org/doi/abs/10.2514/1.J058322
K. Matsuoka, H., Taki, A. Kawasaki, J. Kasahara, H. Watanabe, A. Matsuo, and T. Endo, Semi‐Valveless Pulse
Detonation Cycle at a Kilohertz‐scale Operating Frequency, Combustion and Flame, Vol. 205, 2019, pp. 434‐
440.
https://doi.org/10.1016/j.combustflame.2019.04.035
J. Shepherd, J. Kasahara, Analytical Models for the Thrust of a Rotating Detonation Engine, GALCIT Report
FM2017.001.
https://authors.library.caltech.edu/81786/1/rde_model_report.pdf
A. Kubota, K. Matsuoka, A. Kawasaki, J. Kasahara, H. Watanabe, A. Matsuo, and T. Endo, Optical
Measurement of Fluid Motion in Semi‐Valveless Pulse Detonation Combustor with High‐Frequency

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Operation, Combustion Science and Technology, Vol. 192, 2020, pp.197‐212.
https://doi.org/10.1080/00102202.2018.1559837
K. Goto, J. Nishimura, A. Kawasaki, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki, D. Nakata, M. Uchiumi, K.
Higashino, Experimental Propulsive Performance and Heating Environment of Rotating Detonation Engine
with Various Throat Geometries, Journal of Propulsion and Power, Vol. 35, No. 1, 2019, pp.213‐223.
https://doi.org/10.2514/1.B37196
A. Kawasaki, T. Inakawa, J. Kasahara, K. Goto, K. Matsuoka, A. Matsuo, I. Funaki, Critical Condition of Inner
Cylinder Radius for Sustaining Rotating Detonation Waves in Rotating Detonation Engine Thruster,Proceedings of the Combustion Institute, Vol. 37, No. 3, 2019, pp. 3461‐3469.
https://doi.org/10.1016/j.proci.2018.07.070
M. Yamaguchi, K. Matsuoka, A. Kawasaki, J. Kasahara, H. Watanabe, A. Matsuo, Study on a Reflective
Shuttling Detonation Wave in Fan‐Shaped Two‐Dimensional Combustor, Proceedings of the Combustion
Institute, Vol. 37, No. 3, 2019, pp. 3741‐3747.
https://doi.org/10.1016/j.proci.2018.06.210
K. Matsuoka, S. Takagi, J. Kasahara, A. Matsuo, T. Endo, Validation of Pulse Detonation Operation in Low‐Ambient‐Pressure Environment Journal of Propulsion and Power, Vol. 34, No. 1, 2018, pp.116‐124.
https://doi.org/10.2514/1.B36401
S. Nakagami, K. Matsuoka, J. Kasahara, Y. Kumazawa, J. Fujii, A. Matsuo, I. Funaki, Experimental Visualizationof the Structure of Rotating Detonation Waves in a Disk‐Shaped Combustor, Journal of Propulsion andPower, Vol. 33, No. 1, 2017, pp.80‐88.
https://doi.org/10.2514/1.B36084K. Matsuoka, K. Muto, J. Kasahara, H. Watanabe, A. Matsuo and T. Endo, Development of High‐Frequency
Pulse Detonation Combustor without Purging Material, Journal of Propulsion and Power, Vol. 33, No. 1,
2017, pp.43‐50.
https://doi.org/10.2514/1.B36068
S. Nakagami, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki, Experimental Study of the Structure of Forward‐Tilting Rotating Detonation Waves and Highly Maintained Combustion Chamber Pressure in a Disk‐ShapedCombustor, Proceedings of the Combustion Institute, Vol. 36, No. 2, 2017, pp. 2673‐2680.
https://doi.org/10.1016/j.proci.2016.07.097
K. Matsuoka, K. Muto, J. Kasahara, H. Watanabe, A. Matsuo, T. Endo, Investigation of Fluid Motion inValveless Pulse Detonation Combustor with High‐Frequency Operation, Proceedings of the Combustion
Institute, Vol. 36, No. 2, 2017, pp. 2641‐2647.
https://doi.org/10.1016/j.proci.2016.07.069
K. Matsuoka, T. Morozumi, S. Takagi, J. Kasahara, A. Matsuo, I. Funaki, Flight Validation of a Rotary‐Valved
Four‐Cylinder Pulse Detonation Rocket, Journal of Propulsion and Power, Vol. 32, No. 2, 2016, pp.383‐391.
https://doi.org/10.2514/1.B35739
K. Matsuoka, R. Sakamoto, T. Morozumi, J. Kasahara, A. Matsuo, I. Funaki, Thrust Performance of Rotary‐
Valved Four‐Cylinder Pulse Detonation Rocket Engine, Transaction of the Japan Society for Aeronautical andSpace Sciences, Vol. 58, No. 4, pp. 193‐203, 2015.
https://doi.org/10.2322/tjsass.58.193
H. Nakayama, J. Kasahara, A. Matsuo, and I. Funaki, Front shock behavior of stable curved detonation waves
in rectangular‐cross‐section curved channels, Proceedings of the Combustion Institute, Vol. 34, 2013,
pp.1939‐1947.
https://doi.org/10.1016/j.proci.2012.06.012
H. Nakayama, T. Moriya, J. Kasahara, A. Matsuo, Y. Sasamoto, and I. Funaki, Propagation of Curved
Detonation Waves Stabilized in Annular Channels, Transaction of JSASS Aerospace Technology Japan, 10,
ists28, Pe_7‐14 (2012).
https://doi.org/10.2322/tastj.10.Pe_7
K. Matsuoka, M. Esumi, K. B. Ikeguchi, J. Kasahara, A. Matsuo, and I. Funaki, Experimental Investigation of aMulti‐Cycle Single Tube Pulse Detonation Rocket Engine with a Coaxial Rotary Valve, Transaction of JSASS
Aerospace Technology Japan, 10, ists28, Te_1‐4 (2012).
https://doi.org/10.2322/tastj.10.Te_1

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23. K. Matsuoka, M. Esumi, K. B. Ikeguchi, J. Kasahara, A. Matsuo, and I. Funaki, Optical and Thrust
Measurement of a Pulse Detonation Combustor with a Coaxial Rotary Valve, Combustion and Flame, Vol.
159, 2012, No. 3, pp.1321‐1338.
https://doi.org/10.1016/j.combustflame.2011.10.001
24. H. Nakayama, T. Moriya, J. Kasahara, A. Matsuo, Y. Sasamoto, and I. Funaki, Stable Detonation Wave
Propagation in Rectangular‐Cross‐Section Curved Channels, Combustion and Flame, Vol. 159, 2012, No. 2,pp.859‐869.
https://doi.org/10.1016/j.combustflame.2011.07.022
25. K. Kawane, S. Shimada, J. Kasahara, and A. Matsuo, The Influence of Heat Transfer and Friction on theImpulse of a Detonation Tube, Combustion and Flame , Vol. 158, No. 10, 2011, pp.2023‐2036.
https://doi.org/10.1016/j.combustflame.2011.02.017
26. K. Matsuoka, J. Yageta, T. Nakamichi, J. Kasahara, T. Yajima, T. Kojima, Inflow‐Driven Valve System for Pulse
Detonation Engines, Journal of Propulsion and Power, Vol. 27, No.3, May‐June 2011, pp.597‐607.
https://doi.org/10.2514/1.47421
27. J. Kasahara, M. Hirano, A. Matsuo, Y. Daimon, T. Endo, Thrust Measurement of a Multicycle Partially FilledPulse Detonation Rocket Engine, Journal of Propulsion and Power, Vol.25, No.6, November‐December 2009,
pp.1281‐1290.
https://doi.org/10.2514/1.42224
28. J. Kasahara, A. Hasegawa, T. Nemoto, H. Yamaguchi,T. Yajima , T. Kojima, Performance Validation of a Single‐Tube Pulse Detonation Rocket System, Journal of Propulsion and Power, Vol.25, No.1, January‐February
2009, pp.173‐180.
https://doi.org/10.2514/1.37924
29. J. Kasahara, Z. Liang, S. T. Browne, and J. E. Shepherd, Impulse Generation by an Open Shock Tube, AIAA
Journal, Vol.46, No. 7, 2008, pp.1593‐1603.
https://doi.org/10.2514/1.27467

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