Experimental investigation of momentum and heat transfer in pulse detonation rockets

J. Kasahara, Y. Tanahashi, M. Hirano, T. Numata, Akiko Matsuo, T. Ende

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.

Original languageEnglish
Title of host publicationAIAA Paper
Pages11158-11167
Number of pages10
Publication statusPublished - 2004
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: 2004 Jan 52004 Jan 8

Other

Other42nd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period04/1/504/1/8

Fingerprint

Momentum transfer
Detonation
Rockets
Heat transfer
Heat flux
Enthalpy
Ethylene
Oxygen
Lasers
Sensors

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Kasahara, J., Tanahashi, Y., Hirano, M., Numata, T., Matsuo, A., & Ende, T. (2004). Experimental investigation of momentum and heat transfer in pulse detonation rockets. In AIAA Paper (pp. 11158-11167)

Experimental investigation of momentum and heat transfer in pulse detonation rockets. / Kasahara, J.; Tanahashi, Y.; Hirano, M.; Numata, T.; Matsuo, Akiko; Ende, T.

AIAA Paper. 2004. p. 11158-11167.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Kasahara, J, Tanahashi, Y, Hirano, M, Numata, T, Matsuo, A & Ende, T 2004, Experimental investigation of momentum and heat transfer in pulse detonation rockets. in AIAA Paper. pp. 11158-11167, 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States, 04/1/5.
Kasahara J, Tanahashi Y, Hirano M, Numata T, Matsuo A, Ende T. Experimental investigation of momentum and heat transfer in pulse detonation rockets. In AIAA Paper. 2004. p. 11158-11167
Kasahara, J. ; Tanahashi, Y. ; Hirano, M. ; Numata, T. ; Matsuo, Akiko ; Ende, T. / Experimental investigation of momentum and heat transfer in pulse detonation rockets. AIAA Paper. 2004. pp. 11158-11167
@inproceedings{5e96a5a322cf4202b7a49265187a6a28,
title = "Experimental investigation of momentum and heat transfer in pulse detonation rockets",
abstract = "The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.",
author = "J. Kasahara and Y. Tanahashi and M. Hirano and T. Numata and Akiko Matsuo and T. Ende",
year = "2004",
language = "English",
pages = "11158--11167",
booktitle = "AIAA Paper",

}

TY - GEN

T1 - Experimental investigation of momentum and heat transfer in pulse detonation rockets

AU - Kasahara, J.

AU - Tanahashi, Y.

AU - Hirano, M.

AU - Numata, T.

AU - Matsuo, Akiko

AU - Ende, T.

PY - 2004

Y1 - 2004

N2 - The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.

AB - The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.

UR - http://www.scopus.com/inward/record.url?scp=2942715160&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=2942715160&partnerID=8YFLogxK

M3 - Conference contribution

SP - 11158

EP - 11167

BT - AIAA Paper

ER -