Experimental investigation of momentum and heat transfer in pulse detonation rockets

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

Research output: Contribution to conferencePaper

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
Pages11158-11167
Number of pages10
Publication statusPublished - 2004 Jul 1
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

ASJC Scopus subject areas

  • Engineering(all)

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  • 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. 11158-11167. Paper presented at 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.