Study on a rotary-valved four-cylinder pulse detonation rocket: Thrust measurement by ground test

Tomohito Morozumi; Ryuki Sakamoto; Takashi Kashiwazaki; Ken Matsuoka; Shunsuke Takagi; Jiro Kasahara; Akiko Matsuo; Ikkoh Funaki

doi:10.2514/6.2014-1317

Study on a rotary-valved four-cylinder pulse detonation rocket: Thrust measurement by ground test

Tomohito Morozumi, Ryuki Sakamoto, Takashi Kashiwazaki, Ken Matsuoka, Shunsuke Takagi, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

Department of Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

12 Citations (Scopus)

Abstract

Thrust measurement experiment was carried out using a four-cylinder pulse detonation rocket engine (PDRE) with a rotary valve. The PDRE uses three types of gases, oxidizer, fuel, and purge gas to generate detonation wave intermittently and produces thrust. A rotary valve attached coaxially to a motor for supplying these three gases intermittently was used. The mechanism of the rotary valve is very simple. It is built up with a top cover, a rotating disk, and a casing, and has advantage to enable high mass flow rate and high frequency operation. In this study, pulse detonation rocket (PDR) for flight tests was developed. Thrust measurement experiment by grand test was carried out to check the performance of the this PDR. The oxidizer was N₂O, the fuel was C₂H₄, and the purge gas was He. In the operation time for 1500 msec with C₂H₄-N₂O propellant, we achieved time-averaged thrust of 256 N and specific impulse of 130.8 sec.

Original language	English
Title of host publication	52nd Aerospace Sciences Meeting
Publisher	American Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)	9781624102561
DOIs	https://doi.org/10.2514/6.2014-1317
Publication status	Published - 2014
Event	52nd Aerospace Sciences Meeting 2014 - National Harbor, United States Duration: 2014 Jan 13 → 2014 Jan 17

Publication series

Name	52nd Aerospace Sciences Meeting

Other

Other	52nd Aerospace Sciences Meeting 2014
Country/Territory	United States
City	National Harbor
Period	14/1/13 → 14/1/17

ASJC Scopus subject areas

Aerospace Engineering

Access to Document

10.2514/6.2014-1317

Cite this

Morozumi, T., Sakamoto, R., Kashiwazaki, T., Matsuoka, K., Takagi, S., Kasahara, J., Matsuo, A., & Funaki, I. (2014). Study on a rotary-valved four-cylinder pulse detonation rocket: Thrust measurement by ground test. In 52nd Aerospace Sciences Meeting (52nd Aerospace Sciences Meeting). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2014-1317

Study on a rotary-valved four-cylinder pulse detonation rocket: Thrust measurement by ground test. / Morozumi, Tomohito; Sakamoto, Ryuki; Kashiwazaki, Takashi et al.
52nd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2014. (52nd Aerospace Sciences Meeting).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Morozumi, T, Sakamoto, R, Kashiwazaki, T, Matsuoka, K, Takagi, S, Kasahara, J, Matsuo, A & Funaki, I 2014, Study on a rotary-valved four-cylinder pulse detonation rocket: Thrust measurement by ground test. in 52nd Aerospace Sciences Meeting. 52nd Aerospace Sciences Meeting, American Institute of Aeronautics and Astronautics Inc., 52nd Aerospace Sciences Meeting 2014, National Harbor, United States, 14/1/13. https://doi.org/10.2514/6.2014-1317

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abstract = "Thrust measurement experiment was carried out using a four-cylinder pulse detonation rocket engine (PDRE) with a rotary valve. The PDRE uses three types of gases, oxidizer, fuel, and purge gas to generate detonation wave intermittently and produces thrust. A rotary valve attached coaxially to a motor for supplying these three gases intermittently was used. The mechanism of the rotary valve is very simple. It is built up with a top cover, a rotating disk, and a casing, and has advantage to enable high mass flow rate and high frequency operation. In this study, pulse detonation rocket (PDR) for flight tests was developed. Thrust measurement experiment by grand test was carried out to check the performance of the this PDR. The oxidizer was N2O, the fuel was C2H4, and the purge gas was He. In the operation time for 1500 msec with C2H4-N2O propellant, we achieved time-averaged thrust of 256 N and specific impulse of 130.8 sec.",

author = "Tomohito Morozumi and Ryuki Sakamoto and Takashi Kashiwazaki and Ken Matsuoka and Shunsuke Takagi and Jiro Kasahara and Akiko Matsuo and Ikkoh Funaki",

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AB - Thrust measurement experiment was carried out using a four-cylinder pulse detonation rocket engine (PDRE) with a rotary valve. The PDRE uses three types of gases, oxidizer, fuel, and purge gas to generate detonation wave intermittently and produces thrust. A rotary valve attached coaxially to a motor for supplying these three gases intermittently was used. The mechanism of the rotary valve is very simple. It is built up with a top cover, a rotating disk, and a casing, and has advantage to enable high mass flow rate and high frequency operation. In this study, pulse detonation rocket (PDR) for flight tests was developed. Thrust measurement experiment by grand test was carried out to check the performance of the this PDR. The oxidizer was N2O, the fuel was C2H4, and the purge gas was He. In the operation time for 1500 msec with C2H4-N2O propellant, we achieved time-averaged thrust of 256 N and specific impulse of 130.8 sec.

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Study on a rotary-valved four-cylinder pulse detonation rocket: Thrust measurement by ground test

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