TY - GEN
T1 - Study on Pulse Detonation Rocket Engine using flight test demonstrator “Todoroki II”
AU - Takagi, Shunsuke
AU - Morozumi, Tomohito
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Funding Information:
This study was subsidized by the Research Grant Program from the Institute of Space and Astronautical Science, the Japan Aerospace Exploration Agency, a Grant-in-Aid for Scientific Research (A), No. 24246137. The main structure of the flight vehicle was designed and manufactured by IHI Aerospace Engineering, NETS and Yamamoto Mechanical Design. The authors would like to thank Prof. T. Endo of Hiroshima University, Prof. K. Ishii of Yokohama National University, Prof.Y. Maru ofJAXA/ISAS, Prof.M. Nishioka of University ofTsukuba foradvice about this study and Mr. Y. Saito of Photron Corporation for technical assistance in measuring the trajectory of the flight model. We appreciate cooperation of Mr.T. Kashiwazaki and Mr. Y.Fujiwara.
Publisher Copyright:
© 2014 by Nagoya University. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2014
Y1 - 2014
N2 - A pulse detonation engine (Pulse Detonation Engine, PDE) generates a detonation wave intermittently, and obtains a thrust and work. In this research, the four cylinder pulse detonation rocket engine system “Todoroki II” was developed. The total weight of the flight test demonstrator is 32.5 kg. Moreover, the length is 1910 mm and the diameter of a combustion tube of a pipe in 800 mm is 37 mm. The launch and the recovery system for a flight test were also developed. The flight vehicle is recoveried without damage by winding system. It was proved that the flight test can be done repeatedly. In this flight test, the propellant mass flow estimated is mp=229 g/s. A time average thrust is Fave=254 N, the specific impulse of a propellant base is estimated to be Isp, PF =113 s, this specific impulse is 86 % of a ground test. The attitude of Todoroki incline to the positive direction of pitch up. The some factors of the inclination of Todoroki II are that the number of iginition different in each combustion tube and the attitude of Todoroki II launched is tilted. Considering these factors calculation results agree with experimental results in the attitude of Todoroki II.
AB - A pulse detonation engine (Pulse Detonation Engine, PDE) generates a detonation wave intermittently, and obtains a thrust and work. In this research, the four cylinder pulse detonation rocket engine system “Todoroki II” was developed. The total weight of the flight test demonstrator is 32.5 kg. Moreover, the length is 1910 mm and the diameter of a combustion tube of a pipe in 800 mm is 37 mm. The launch and the recovery system for a flight test were also developed. The flight vehicle is recoveried without damage by winding system. It was proved that the flight test can be done repeatedly. In this flight test, the propellant mass flow estimated is mp=229 g/s. A time average thrust is Fave=254 N, the specific impulse of a propellant base is estimated to be Isp, PF =113 s, this specific impulse is 86 % of a ground test. The attitude of Todoroki incline to the positive direction of pitch up. The some factors of the inclination of Todoroki II are that the number of iginition different in each combustion tube and the attitude of Todoroki II launched is tilted. Considering these factors calculation results agree with experimental results in the attitude of Todoroki II.
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U2 - 10.2514/6.2014-4033
DO - 10.2514/6.2014-4033
M3 - Conference contribution
AN - SCOPUS:84913535511
T3 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
BT - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
Y2 - 28 July 2014 through 30 July 2014
ER -